TCDS A14CE

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Rev. No. 41 28 32 30 28 28 30 32 30 30 30 35 32 34 30 36 40 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A14CE Revision 41 Textron Aviation 99 100 99A A100 99A (U-21F) (FACH) A100A A99 A100C A99A B100 B99 C99 November 27, 2017 TYPE CERTIFICATE DATA SHEET NO. A14CE This data sheet which is part of Type Certificate No. A14CE prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Textron Aviation Inc. One Cessna Boulevard Wichita, Kansas 67215 Type Certificate Holder Record: Beech Aircraft Corporation to Raytheon Aircraft Company on April 15, 1996 Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 Hawker Beechcraft Corporation transferred to Beechcraft Corporation on April 12, 2013 Beechcraft Corporation transferred to Textron Aviation Inc. on October 12, 2016 I. Model 99, Airliner, (Normal Category), Approved May 2, 1968 Model 99A, Airliner, (Normal Category), Approved February 10, 1969 Military 99A(FACH), (Normal Category), Approved June 10, 1970 Engines Two (2) United Aircraft of Canada, Ltd. PT6A-20 (Turboprop) per Beech Specification BS 20331A (99). OR Two (2) United Aircraft of Canada, Ltd. or Pratt and Whitney PT6A-27 (Turboprop) per Beech Specification BS 20570B (99A). See NOTE 6 OR Two (2) UACL or Pratt and Whitney PT6A-28 (Turboprop) per Beech Specification BS 21404 (99A). See NOTE 8 Fuel JP-4, JP-5 (MIL-T-5624); JP-8 (MIL-T-83133); JET A, JET A-1 & JET B conforming to P&WC S.B. 1244 or ASTM SPEC. D1655. See NOTE 7 for emergency fuels Oil (Engine and Gearbox) UACL PT6 Service Bulletin No. 1 lists approved brand oils. Engine limits*** Static Sea Level Ratings PT6A-20 Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft Speed Maximum Permissible Turbine Interstage Temp (Deg.C.) Takeoff (5 min.) 550** 72 579 2200* 750 Maximum continuous 550** 72 579 2200* 750 Starting trans. (2 sec.) 1090 Max. reverse (1 min.) 300 2100 750 *See NOTE 4 **Available to 70 F. (21.2 C.) static ***See NOTE 9 A14CE Page 2 of 17 Rev. 41 I. Model 99, Model 99A, Military 99A (cont’d) Engine Limits*** Static Sea Level Ratings PT6A-27 or -28 Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft Speed Maximum Permissible Turbine Interstage Temp(Deg.C.) Takeoff (5 min.) 550** 76 580 2200* 725 Maximum continuous 550** 76 580 2200* 725 Starting trans. (2 sec.) 1090 Max. reverse (1 min.) 300 2100 725 *See NOTE 4 **Available to 112.4 F. (44.6 C.) static ***See NOTE 9 Oil temperatures: Minus 40° F. Minimum starting Minus 40° F. to 210°F. Low idle 50° F. to 210° F. Maximum continuous Propeller and Two (2) Hartzell HC-B3TN-3 or HC-B3TN3B hubs with Hartzell T10173E-8 Propeller Limits or T10173B-8 blades Diameter: 93 3/8 in. (normal); minimum allowable for repair 90 3/8 in. No further reduction permitted Pitch settings at 30 in. sta.: Reversing propeller Flight idle stop See NOTE 5 Second flight idle stop See NOTE 5 Reverse - 11° Feather - 87° Airspeed Limits (CAS) Max. operating speed 260 mph (226 knots) up to 15,500 ft. 15,500 ft. to 25,000 ft. decrease 4 knots per 1,000 ft. Maneuvering speed 195 mph (169 knots) *Flaps extended speed 152 mph (132 knots) Landing gear extended 180 mph (156 knots) Landing gear 150 mph (130 knots) (Retraction) Operating 180 mph (156 knots) (Extension) *See NOTE 9. C.G. Range (Landing (+179.0) to (+195.0) at 10,400 lb. or less Gear Extended) Moment change due to retracting landing gear -4871 in.-lb. 178 180 182 184 186 188 190 192 194 196 5400 5800 6200 6600 7000 7400 7800 8200 8600 9000 9400 9800 10200 10600 INCHES LB. REAR LIMIT FWD LIMIT A14CE Page 3 of 17 Rev. 41 I. Model 99, Model 99A, Military 99A (cont’d) Empty Wt. C.G. Range None *Maximum Weight Takeoff 10,400 lb. Landing 10,400 lb. *See NOTE 9 No. of Seats Maximum 17 (including 2 crew seats at +126) See loading instructions in Pilot's Operating Handbook for an approved seating or cargo configuration. FAA approval for any other configuration must be obtained. Maximum Baggage 600 lb. (+ 52) 100 lb. (+378) 800 lb. (+187) in baggage pod when installed Fuel Capacity 115 gal. (+160) (total usable in 2 nacelle tanks, 57 gal. each) 258 gal. (+196) (total usable in 2 wing tanks 128 gal. each) See NOTE 1(a) for data on system fuel Oil Capacity 28 qt. (total oil capacity) (includes 12 qt. usable in 2 integral engine tanks at +131) See NOTE 1(b) for data on system oil Maximum Operating 25,500 ft. Altitude For FAR 91 operations: without oxygen 12,000 ft. with crew oxygen only 15,000 ft. For FAR 135 operations: as limited by FAR 135.83 Control Surface Movements Wing flaps Maximum 43° Aileron tab Up 15° Down 15° Aileron Up 18° Down 20° Elevator Up 12° Down 15° *Stabilizer Up 3-1/2° Down 3-1/2° Rudder tab Right 30° Left 30° Rudder Right 26° Left 20° *See NOTE 9 Serial Nos. Eligible U-1 through U-145 and U-147 See NOTE 6 II. Model 100, King Air, (Normal Category), Approved July 24, 1969 Engines Two (2) United Aircraft of Canada, Ltd. or Pratt and Whitney PT6A-28 (Turboprop) per Beech Specification BS 21404 Fuel JP-4, JP-5 (MIL-T-5624); JP-8 (MIL-T-83133); JET A, JET A-1, & JET B conforming to P&WC S.B. 1244 or ASTM SPEC. D1655. See NOTE 7 for emergency fuels Oil (Engine and Gearbox) UACL PT6 Service Bulletin No. 1 lists approved brand oils. A14CE Page 4 of 17 Rev. 41 II. Model 100 (cont’d) Engine Limits*** Static Sea Level Ratings Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft Speed Maximum Permissible Turbine Interstage Temp (Deg.C.) Takeoff (5 min.) 680** 90 715 2200* 750 Maximum continuous 680** 90 715 2200* 750 Starting trans. (2 sec.) 1090 Max. reverse (1 min.) 300 2100 750 *See NOTE 4 **Available to 70 F. (21.2 C.) static 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 those conditions the placarded torquemeter limitations shall not be exceeded. Oil temperatures: Minus 40° F. Minimum starting Minus 40° F. to 210°F. Low idle 50° F. to 210° F. Max. continuous Propeller and Two (2) Hartzell HC-B3TN-3 or HC-B3TN-3B or HC-B3TN-3M hubs with Hartzell Propeller Limits T10173E-8 or T10173B-8 or T10173NB-8 blades. Diameter: 93-3/8 in. (normal); minimum allowable for repair 90-3/8 in. No further reduction permitted Pitch settings at 30 in. sta.: Flight idle stop See NOTE 5 Secondary flight idle stop See NOTE 5 Reverse - 11° Feather - 87° Airspeed Limits (CAS) Max. operating speed 260 mph (226 knots) up to 15,500 ft. Decrease 4 knots per 1,000 ft. above 15,500 ft. Maneuvering speed 195 mph (169 knots) Max. flaps extension speed Approach position 13° 210 mph (182 knots) Full down position 43° 161 mph (140 knots) Landing gear extended 180 mph (156 knots) Landing gear operating 180 mph (156 knots) (Extension) 150 mph (130 knots) (Retraction) C.G. Range (Landing (+181.0) to (+191.0) at 10,600 lb. or less Gear Extended) (+177.0) to (+191.0) at 9,580 lb. or less Straight line variation between points given Moment change due to retracting landing gear -4845 in.-lb. 174 176 178 180 182 184 186 188 190 192 7600 7800 8000 8200 8400 8600 8800 9000 9200 9400 9600 9800 10200 10600 INCHES LB. 10800 A14CE Page 5 of 17 Rev. 41 II. Model 100 (cont’d) Empty Wt. C.G. Range None *Maximum Weight Ramp 10,688 lb. Takeoff 10,600 lb. Landing 10,600 lb. No. of Seats Maximum 15 (including 2 crew seats at +129) See loading instructions in Pilot's Operating Handbook for an approved seating or cargo configuration. FAA approval for any other configurations must be obtained. Maximum Baggage 355 lb. (+292); 410 lb. (+325) Extra equipment installed in or aft of this area may reduce limit to below placarded figure. Fuel Capacity 115 gal. (+161) (total usable in 2 nacelle tanks, 57 gal. each) 258 gal. (+197) (total usable in 2 wing tanks 130 gal. each) See NOTE 1(a) for data on system fuel Oil Capacity 28 qt. total (includes 12 qt. usable in 2 integral tanks at (+131)). See NOTE 1(b) for data on system oil Maximum Operating Altitude 31,000 ft. Control Surface Wing flaps Maximum 43° Movements Aileron tab Up 15° Down 15° Aileron Up 16° Down 22° Elevator Up 15° Down 15° Horizontal stabilizer Up 4-1/2° Down 4° (at leading edge) Rudder tab Right 30° Left 30° Rudder Right 25° Left 20° Serial Nos. Eligible B-2 through B-89 and B-93 III. Model A99, Airliner (Normal Category), Approved February 19, 1971 Engines Two (2) United Aircraft of Canada, Ltd. PT6A-20 (Turboprop) per Beech Specification BS 20331A. See NOTE 6 Fuel JP-4, JP-5 (MIL-T-5624); JP-8 (MIL-T-83133); JET A, JET A-1, & JET B conforming to P&WC S.B. 1244 or ASTM SPEC. D1655. See NOTE 7 for emergency fuels Oil (Engine & Gearbox) UACL PT6 Service Bulletin No. 1 lists approved brand oils. Engine Limits Static Sea Level Ratings PT6A-20 Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft Speed Maximum Permissible Turbine Interstage Temp (Deg.C.) Takeoff (5 min.) 550** 72 579 2200* 750 Maximum continuous 550** 72 579 2200* 750 Starting trans. (2 sec.) 1090 Max. reverse (1 min.) 300 2100 750 *See NOTE 4 **Available to 70 F. (21.2 C.) static Oil temperatures: Minus 40° F. Minimum starting Minus 40° F. to 210°F. Low idle 50° F. to 210° F. Max. continuous A14CE Page 6 of 17 Rev. 41 III. Model A99 (cont’d) Propeller and Two (2) Hartzell HC-B3TN-3 or HC-B3TN-3B hubs with Hartzell T10173E-8 or Propeller Limits T10173B-8 blades. Diameter: 93-3/8 in. (normal); minimum allowable for repair 90-3/8 in. No further reduction permitted Pitch settings at 30 in. sta.: Reversing propeller: Flight idle stop See NOTE 5 Secondary flight idle stop See NOTE 5 Reverse - 11° Feather - 87° Airspeed Limits (CAS) Max. operating speed 260 mph (226 knots) up to 15,500 ft. 15,500 ft. to 25,000 ft. decrease 4 knots per 1,000 ft. Maneuvering speed 195 mph (169 knots) Flaps extended speed 161 mph (140 knots) Landing gear extended 180 mph (156 knots) Landing gear operating 150 mph (130 knots) (Retraction) 180 mph (156 knots) (Retraction) C.G. Range (Landing (+179.0) to (+195.0) at 10,650 lb. or less Gear Extended) Moment change due to retracting landing gear -4871 in.-lb. Empty Wt. C.G. Range None *Maximum Weight Ramp 10,705 lb. Takeoff 10,650 lb. Landing 10,650 lb. Maximum Zero Fuel Weight 9900 lb. (All weight above 9900 lb. must be in fuel weight) No. of Seats Maximum 17 (including 2 crew seats at +126) See loading instructions in Pilot's Operating Handbook for an approved seating or cargo configuration. FAA approval for any other configurations must be obtained. Maximum Baggage 600 lb. (+ 52) 100 lb. (+378) 800 lb. (+187) in baggage pod when installed. Fuel Capacity 257 gal. (+181) (total usable in 2 wing tanks, 127 gal. each) See NOTE 1(a) for data on system fuel Oil Capacity 28 qt. total (includes 12 qt. usable in 2 integral tanks at (+131)). See NOTE 1(b) for data on system oil Maximum Operating Altitude 25,000 ft. For FAR 91 operations: without oxygen 12,500 ft. with crew oxygen only 15,000 ft. For FAR 135 operations: As limited by FAR 135.83 Control Surface Wing flaps Maximum 43° Movements Aileron tab Up 15° Down 15° Aileron Up 18° Down 22° Elevator Up 12° Down 15° Stabilizer Up 4-1/4° Down 3-1/2 Rudder tab Right 30° Left 30° Rudder Right 26° Left 20° Serial Nos. Eligible U-1 through U-145 and U-147 A14CE Page 7 of 17 Rev. 41 IV. Model A99A, Airliner (Normal Category), Approved February 19, 1971 Engines Two (2) United Aircraft of Canada, Ltd. or Pratt and Whitney PT6A-27 or -28 (Turboprop) per Beech Specification BS 20570B or BS 21404 . See NOTE 8 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 7 for emergency fuels Oil (Engine & Gearbox) UACL PT6 Service Bulletin No. 1 lists approved brand oils. Engine Limits Static Sea Level Ratings PT6A-27 or -28 Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft Speed Maximum Permissible Turbine Interstage Temp (Deg.C.) Takeoff (5 min.) 680** 76 715 2200* 725 Maximum continuous 680** 76 715 2200* 725 Starting trans. (2 sec.) 1090 Max. reverse (1 min.) 300 2100 725 *See Note 4 **Available to 70 F. (21.2 C.) static Oil temperatures: Minus 40° F. Minimum starting Minus 40° F. to 210°F. Low idle 50° F. to 210° F. Max. continuous Propeller and Two (2) Hartzell HC-B3TN-3 or HC-B3TN-3B hubs with Hartzell T10173E-8 or Propeller Limits T10173B-8 blades. Diameter: 93-3/8 in. (normal); minimum allowable for repair 90-3/8 in. No further reduction permitted Pitch settings at 30 in. sta.: Reversing propeller: Flight idle stop See NOTE 5 Secondary flight idle stop See NOTE 5 Reverse - 11° Feather - 87° Airspeed Limits (CAS) Max. operating speed 260 mph (226 knots) up to 15,500 ft. 15,500 ft. to 25,000 ft. decrease 4 knots per 1,000 ft. Maneuvering speed 195 mph (169 knots) Flaps extended speed 161 mph (140 knots) Landing gear extended 180 mph (156 knots) Landing gear operating 150 mph (130 knots) (Retraction) 180 mph (156 knots) (Retraction) C.G. Range (Landing (+179.0) to (+195.0) at 10,900 lbs. or less Gear Extended) Moment change due to retracting landing gear -4871 in.-lb. Empty Wt. C.G. Range None *Maximum Weight Ramp 10,955 lb. Takeoff 10,900 lb. Landing 10,900 lb. Maximum Zero Fuel Weight 9900 lb. (All weight above 9900 lb. Must be in fuel weight) No. of Seats Maximum 17 (including 2 crew seats at +126) See loading instructions in Pilot's Operating Handbook for an approved seating or cargo configuration. FAA approval for any other configurations must be obtained. A14CE Page 8 of 17 Rev. 41 IV. Model A99A (cont’d) Maximum Baggage 600 lb. (+ 52) 100 lb. (+378) 800 lb. (+187) in baggage pod when installed. Fuel Capacity 257 gal. (+181) (total usable in 2 wing tanks 127 gal. each) See NOTE 1(a) for data on system fuel Oil Capacity 28 qt. total (includes 12 qt. usable in 2 integral tanks at (+131)). See NOTE 1(b) for data on system oil Maximum Operating Altitude 25,000 ft. For FAR 91 operations: without oxygen 12,500 ft. with crew oxygen only 15,000 ft. For FAR 135 operations: As limited by FAR 135.83 Control Surface Wing flaps Maximum 43° Movements Aileron tab Up 15° Down 15° Aileron Up 18° Down 20° Elevator Up 12° Down 15° Stabilizer Up 4-1/4° Down 3-1/2 Rudder tab Right 30° Left 30° Rudder Right 26° Left 20° Serial Nos. Eligible U-1 through U-145 and U-147 V. Model A100, King Air (Military U-21F) (Normal Category), Approved May 7, 1971 Engines Two (2) United Aircraft of Canada, Ltd. or Pratt and Whitney PT6A-28 (Turboprop) per Beech Specification BS 21404 or; Two (2) United Aircraft of Canada, Ltd. or Pratt and Whitney PT6A-34 (Turboprop) per Pratt and Whitney Specification No. 735. Fuel JP-4, JP-5 (MIL-T-5624); JP-8 (MIL-T-83133); JET A, JET A-1, & JET B conforming to P&WC S.B. 1244 or ASTM SPEC. D1655. See NOTE 7 for emergency fuels Oil (Engine & Gearbox) Pratt & Whitney Canada Service Bulletin No. 1001 lists approved oils. Engine Limits Static Sea Level Ratings PT6A-28 Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft Speed Maximum Permissible Turbine Interstage Temp (Deg.C.) Takeoff (5 min.) 680** 90 715 2200* 750 Maximum continuous 680** 90 715 2200* 750 Starting trans. (2 sec.) 1090 Max. reverse (1 min.) 300 2100 750 *See Note 4. **Available to 70 F. (21.2 C.) static 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. A14CE Page 9 of 17 Rev. 41 V. Model A100 (cont’d) Engine Limits Static Sea Level Ratings PT6A-34 Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft Speed Maximum Permissible Turbine Interstage Temp (Deg.C.) Takeoff (5 min.) 680** 87 715 2200* 790 Maximum continuous 680** 87 715 2200* 790 Starting trans. (2 sec.) 1090 Max. reverse (1 min.) 300 2100 790 *See NOTE 4. **Available to 87 F. (30 C.) static 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° F. Minimum starting Minus 40° F. to 210°F. Low idle 50° F. to 210° F. Max. continuous not to exceed 5 min. Propeller and 2 Hartzell HC-B4TN-3 or HC-B4TN-3A hubs with Hartzell T10173-12 ½, Propeller Limits T10173FB-12.5 or T10173FNB-12.5 blades. Diameter: 90 in. (normal) No further reduction permitted Pitch settings at 30 in. sta.: Reversing propeller: Flight idle stop See NOTE 5 Secondary flight idle stop See NOTE 5 Reverse - 11° Feather - 86.5° Airspeed Limits (CAS) Max. operating speed 260 mph (226 knots) up to 15,500 ft. Decrease 4 knots per 1,000 ft. above 15,500 ft. Maneuvering speed 195 mph (169 knots) Maximum flap extension speed Approach position 13 210 mph (182 knots) Full down position 43 161 mph (140 knots) Landing gear extended 180 mph (156 knots) Landing gear operating 180 mph (156 knots) (Extension) 150 mph (130 knots) (Retraction) (S/N B-1, B-90 through B-92, B-94 through B-151) OR 168 mph (146 knots) (Retraction) (S/N B-152 and On) C.G. Range (Landing (+184.5) to (+191.0) at 11,500 lb. Gear Extended) (+177.0) to (+191.0) at 9,580 lb. or less Straight line variation between points given. Moment change due to retracting landing gear -4845 in.-lb. Empty Wt. C.G. Range None *Maximum Weight Ramp 11,568 lb. Takeoff 11,500 lb. Landing 11,210 lb. Maximum zero fuel 9,600 lb. No. of Seats Maximum 15 (including 2 crew seats at +129) See loading instructions in Pilot's Operating Handbook for an approved seating or cargo configuration. FAA approval for any other configurations must be obtained. Maximum Baggage 355 lb. (+292) 410 lb. (+325) Extra equipment installed in or aft of this area may reduce limit to below placarded figure. A14CE Page 10 of 17 Rev. 41 V. Model A100 (cont’d) Fuel Capacity 82 gal. (+204) (2 auxiliary tanks 41 gal. ea.); 388 gal. (+183) (2 main tanks interconnected 194 gal. each) See NOTE 1(a) for data on system fuel. Oil Capacity 28 qt. total (includes 12 qt. usable in 2 integral tanks at (+131)). See NOTE 1(b) for data on system oil. Maximum Operating Altitude 31,000 ft. Control Surface Wing flaps Maximum 43° Movements Aileron tab Up 15° Down 15° Aileron Up 16° Down 22° Elevator Up 15° Down 15° Stabilizer Up 4-1/4° Down 4      at leading edge) Rudder tab Right 30° Left 30° Rudder Right 25° Left 20° Serial Nos. Eligible B-1, B-90 through B-92, B-94 and on. Prior to Civil Certification, Model A100 (U-21F) airplanes, S/N B-95 through B-99 must be modified per Beech Drawing 100-005002. VI. Model B99, Airliner (Normal Category), Approved March 27, 1972 Engines Two (2) United Aircraft of Canada, Ltd. or Pratt and Whitney PT6A-27 or -28 (Turboprop) per Beech Specification BS 20570B, or BS 21404. See NOTE 8 Fuel JP-4, JP-5 (MIL-T-5624); JP-8 (MIL-T-83133); JET A, JET A-1, & JET B conforming to P&WC S.B. 1244 or ASTM SPEC. D1655. See NOTE 7 for emergency fuels Oil (Engine & Gearbox) UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils. Engine Limits Static Sea Level Ratings PT6A-27 or -28 Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft Speed Maximum Permissible Turbine Interstage Temp (Deg.C.) Takeoff (5 min.) 680** 76 715 2200* 725 Maximum continuous 680** 76 715 2200* 725 Starting trans. (2 sec.) 1090 Max. reverse (1 min.) 300 2100 725 *See NOTE 4. **Available to 70 F. (21 C.) static Oil temperatures: Minus 40° F. Minimum starting Minus 40° F. to 210°F. Low idle 50° F. to 210° F. Max. continuous Propeller and Two (2) Hartzell HC-B3TN-3 or HC-B3TN-3B hubs with Hartzell T10173E-8 blades. Propeller Limits Diameter: 93-3/8 in. (normal); minimum allowable for repair 90-3/8 in. No further reduction permitted Pitch settings at 30 in. sta.: Reversing propeller: Flight idle stop See NOTE 5 Secondary flight idle stop See NOTE 5 Reverse - 11° Feather - 87° A14CE Page 11 of 17 Rev. 41 VI. Model B99 (cont’d) Airspeed Limits (CAS) Max. operating speed 260 mph (226 knots) up to 15,500 ft. 15,500 ft. to 25,000 ft. decrease 4 knots per 1,000 ft. Maneuvering speed 195 mph (169 knots) Flaps extended speed Full (100 percent) 161 mph (140 knots) Approach and Takeoff (30 percent) 209 mph (182 knots) Landing gear extended 180 mph (156 knots) Landing gear operating 150 mph (130 knots) (Retraction) 180 mph (156 knots) (Retraction) C.G. Range (Landing (+179.0) to (+195.0) at 10,900 lbs. or less Gear Extended) Moment change due to retracting landing gear -4871 in.-lb. Empty Wt. C.G. Range None *Maximum Weight Ramp 10,955 lb. Takeoff 10,900 lb. Landing 10,900 lb. No. of Seats Maximum 17 (including 2 crew seats at +126 See loading instructions in Pilot's Operating Handbook for an approved seating or cargo configuration. FAA approval for any other configurations must be obtained. Maximum Baggage 600 lb. (+ 52) 100 lb. (+378) 800 lb. (+187) in baggage pod when installed. Fuel Capacity 115 gal. (+160) (Total usable in 2 nacelle tanks, 56 gal. each) 258 gal. (+196) (Total usable in 2 wing tanks 128 gal. each) See NOTE 1(a) for data on system fuel Oil Capacity 28 qt. total (includes 12 qt. usable in 2 integral tanks at (+131)). See NOTE 1(b) for data on system oil Maximum Operating Altitude 25,000 ft. For FAR 91 operations: without oxygen 12,500 ft. with crew oxygen only 15,000 ft. For FAR 135 operations: As limited by FAR 135.83 Control Surface Wing flaps Maximum 43° Movements Aileron tab Up 15° Down 15° Aileron Up 18° Down 20° Elevator Up 12° Down 15° Horizontal Stabilizer Up 4-1/4° Down 3-1/2 Rudder tab Right 30° Left 30° Rudder Right 26° Left 20° Serial Nos. Eligible U-146, U-148 through U-164 VII. Model A100A, King Air, (Normal Category), Approved November 1, 1972 (This section was removed from the TCDS at Revision 39 since no airplanes have been built, nor are any planned to be made). VIII. Model A100C, King Air, (Normal Category), Approved December 14, 1973 (This section was removed from the TCDS at Revision 27 since no airplanes have been built, nor are any planned to be made.) A14CE Page 12 of 17 Rev. 41 IX. Model B100, King Air, (Normal Category), Approved December 1, 1975 Engines Two (2) AiResearch TPE 331-6-252B (Turboprop) per Beech Specification 22558 Fuel Aviation turbine fuels ASTM Designation D1655-68, Types Jet A, Jet B, & Jet A-1; MIL-F-5616-1, Grade JP-1; and MIL-T-5624G-1, Grades JP-4 and JP-5; and MIL-F-46005A(MR)-1, Types I and II. Fuels shall conform to the specifications as listed or to subsequent revisions thereto. See NOTE 7 for use of emergency fuel