# TCDS A14CE: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 41
- Revised: November 27, 2017
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23, Part 36, Part 135
- Registered aircraft: 182, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/f5/9f/f59f8100b8104a9663ffb8d06714c8b59cde5c211992050c2ced1773583bf1fa
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/9A2F3BD921F17D59862581EF005D564C.0001
- Page: https://openairdocs.org/tcds/A14CE

## Models (12)

As the data sheet lists them.

- 99A (FACH)
- A100C
- A99
- A100A
- A99A
- C99
- B99
- B100
- A100 (King Air (Military U-21F))
- 100
- 99A (Airliner, Military 99A (FACH))
- 99

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 
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 
 
 Oil  MIL-23699B and MIL-L-7808G (Oils shall conform to the specifications 
  as listed or to the subsequent revisions thereto.) 
    
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.) 715 153 776 2000 923 
Maximum continuous 715 153 776 2000 923 
Starting trans. (2 sec.)     1149 
Max. reverse (1 min.)    2000  
 
  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° C. to 110 C. Normal operations 
   Minus 40° C. to 110° C. Ground idle 
   Minus 40° C. to 110° C. Takeoff or climb power 
    for 5-minute maximum 
 
 Propeller and  (For Aircraft S/N BE-1 through BE-113): 
   Propeller Limits Two (2) Hartzell HC-B4TN-5C or HC-B4TN-5F hubs with Hartzell T10173FB-12.5 
  or T10173FNB-12.5 aluminum alloy blades and Hartzell D3434-4P or D3434-10P 
  spinner assembly. 
   
  (For Aircraft S/N BE-114 and on): 
  Two (2) Hartzell HC-B4TN-5C or HC-B4TN-5F hubs with Hartzell T10173FK-12.5 
  or T10173FNK-12.5 aluminum alloy blades and Hartzell D3434-4P spinner assembly. 
 
  Diameter:  90 in. (normal); no further reduction permitted. 
  Pitch settings at 30 in. sta.: 
   Feathered +87 
   Reverse pitch stop -10 
   Start locks + 2.5 
   Flight idle + 8.5 
 
 Airspeed Limits (CAS) Max. operating speed 256 mph (223 knots) 
   Decrease 4 knots per 1,000 ft. above 15,500 ft. 
  Max. design maneuver 192 mph (167 knots) 
  Max. flaps extended (30 percent approach)  
   206 mph (179 knots) 
  Max. flap extended (100 percent full down) 
   176 mph (153 knots)  
  Landing gear extended 176 mph (153 knots) 
  Landing gear operating 176 mph (153 knots) 
 
 C.G. Range (Landing (+181.75) to (+191.0) at 11,800 lb.  
   Gear Extended) (+175.0) to (+191.0) at 9,100 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 11,875 lb. 
  Takeoff 11,800 lb. 
  Landing 11,210 lb. 
  Maximum zero fuel   9,600 lb.

A14CE Page 13 of 17 Rev. 41 
IX.  Model B100    (cont’d) 
 
 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 150 lb.   (+292) 
  410 lb.   (+325) 
 
 Fuel Capacity Tank Cap. (Gal.) Usable (Gal.) Arm 
  L & R Main 194+ 194 each (+183.0) 
  L & R Aux.   41+   41 each (+204.0) 
 
  See NOTE 1(d) on System Fuel. 
 
 Oil Capacity 21 qt. total (includes 8 qt. usable in 2 integral tanks at (+207)).  
  See NOTE 1(c) 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° (at leading edge) 
  Horizontal stabilizer Up   4-1/4° Down   4° 
  Rudder tab Right 30° Left 30° 
  Rudder Right 25° Left 20° 
   
   
 Serial Nos. Eligible BE-1 and on 
 
 
X. Model C99, Airliner, (Normal Category), Approved July 27, 1981 
 
 Engines Two (2) United Aircraft of Canada, Ltd. or Pratt and Whitney PT6A-36 
  (Turboprop) per Beech Specification 23365  
 
 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 
 
EngineLlimits*** Static Sea Level Ratings PT6A-36 
  
 
 
Shaft 
Horsepower 
 
 
 
Jet 
Thrust 
 
 
Equivalent 
Shaft  
Horsepower 
 
 
 
Prop Shaft 
Speed 
Maximum 
Permissible 
Turbine 
Interstage 
Temp (Deg.C.) 
Takeoff (5 min.) 715** 85 749 2200* 805 
Maximum continuous 715** 85 749 2200* 805 
Starting trans. (2 sec.)     1090 
Max. reverse (1 min.) 300   2100 805 
  *See Note 4 
  **Available to 103 F. (39 C.) static 
 
  Oil temperatures: Minus 40° F. Minimum starting 
   Minus 40° F. to 210°F. Low idle 
   50° F. to 210° F. Max. continuous 
   210 F. to 220F. 10 min.

A14CE Page 14 of 17 Rev. 41 
 
X. Model C99    (cont’d) 
 
 Propeller and  One (1) or Two (2) Hartzell HC-B3TN-3B and/or One (1) or Two (2) HC-B3TN-3M 
   Propeller Limits hubs with Hartzell 0173K-8 blades.   
  See NOTE 10 
  Diameter: 93-3/8 in. (normal); minimum allowable for repair 90-3/8 in.   
  No further reduction permitted 
  Pitch settings at 30-n sta.: 
  Reversing propeller: 
   Flight Idle Stop See portion of NOTE 5 
   Reverse - 11° 
   Feather  - 87° 
 
 Airspeed Limits (CAS) Max. operating speed 258 mph (224 knots) up to 15,500 ft. 
   15,500 ft. to 25,000 ft. decrease 4 knots per 1,000 ft.  
  Maneuvering speed 190 mph (166 knots) 
  Flaps extended speeds 
    Full (100 percent) 161 mph (140 knots) 
    Approach and takeoff 
      (30 percent) 205 mph (178 knots) 
  Landing gear extended 175 mph (152 knots) 
  Landing gear operating 175 mph (152 knots) (Extension) 
   175 mph (152 knots) (Retraction) 
 
 C.G. Range (Landing (+182.5) to (+195.0) at 11,300 lbs. or less  
   Gear Extended) (+179.0) to (+195.0) at 10,900 lbs. or less  
  Straight line variation between points given 
  Moment change due to retracting landing gear -4871 in.-lb. 
 
 Empty Wt. C.G. Range None 
 
 Maximum Weight Ramp 11,380 lb. 
  Takeoff 11,300 lb. 
  Landing 11,300 lb. 
 
 No. of Seats Maximum 17 (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 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 oil capacity) (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. 
 
 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-50, U-165 and On

A14CE Page 15 of 17 Rev. 41 
Data Pertinent to All Models 
 
 Datum Located +190 in. forward of wing main (forward spar centerline). 
 
 Leveling Means Two external screws on left side of fuselage forward of entrance door. 
 
 Certification Basis        
 99, 99A,  
A99, A99A B99 C99 100 A100 A100A B100 
 Part 23 of the Federal Aviation  
 Regulations dated Feb 1, 1965, as  
 amended by 23-1, 23-2, and 23-3 
X X X X X X X 
 and Par. 23.954 or Am. 23-7     X X X 
 and Par. 23.959 of Am. 23-7  X X   X X 
 and Par. 23.1385(c), 23.1387(a)  
   and 23.1387(e) of Am. 23-12 X X X X X X X 
 and Par. 23.729 of Am. 23-21 X X X     
 and Par. 23.967(a)(5) of Am. 23-18   X     
 and Par. 23.1545(a) of Am. 23-23  
   and 23.1583(a) of Am. 23-7   X     
 and Par. 23.1419 of Am. 23-14       X 
 Par. 25.777 of FAR 25 in effect on  
   April 4, 1969    X X X  
 Part 36 of the Federal Aviation  
   Regulations dated Dec 1, 1969, as 
   amended through 36-10 
  X    X 
 SFAR 27 effective February 1, 1974   X    X 
 Equivalent Safety findings: 
   FAR 23.621 
   FAR 23.729(e) 
   FAR 23.967(a)(5) 
   FAR 23.1323, 23.1545, 23.1583(a)  
 
X 
 
X 
 
X 
 
X 
 
X 
 
X 
 
X 
 
X 
 
X 
X 
X 
X 
 Approved for flight into known icing 
   conditions when equipped per AFM X X X X X X X 
 Special conditions as outlined in FAA 
   letters to Beech dated April 24, 1968 
   (FAR 135) and July 17, 1969 (FAR 91) 
X X X     
 Special conditions as outlined in FAA 
   letter to Beech dated July 19, 1969, and 
   November 6, 1969 (FAR 91 operation 
   only) 
   X X X X 
 Special conditions 23-98-CE-13 issued 
   July 24, 1980 X X X X X X X 
 Special condition A-11, “De-icers FAR 23.1419” for Models 99, 99A, A99, A99A, 99A (FACH), B99 and C99 is 
 equivalent to Sec. 34 “Ice Protection” of SFAR 23 dated January 7, 1969, and Para. 23.1419 of Amendment 23 -14. 
        
 Application for Type Certificate dated July 8, 1966. 
 Type Certificate No. A14CE issued May 2, 1968, obtained by the manufacturer under delegation option procedures.

A14CE Page 16 of 17 Rev. 41 
 
Data Pertinent to All Models  (cont’d) 
 
 Production Basis Production Certificate No. 8.  Delegation Option Manufacturer No. CE-2 authorized to  
  issue airworthiness certificates under delegation option provisions of Part 21 of the  
  Federal Aviation Regulations. 
 
 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations  
  (see Certification Basis) must be installed in the aircraft for certification. 
 
  In addition, the following equipment is required: 
    1. Pre-stall warning indicator, Safe Flight Instrument Corp. 
     Models 99, 99A, A99, A99A (not equipped for operation in icing conditions)  
     P/N 793-1/795-1/795-6 
 
     Models 99, 99A, A99, A99A (equipped for operation in icing conditions)  
     P/N 795-1/795-6 
 
     Model B99 P/N 795-6/795-1 
     Model 100 P/N 795-1/795-6 
     Models A100 (U-21F) and A100A P/N 796-5/795-9 
     Model B100 P/N 795-13 
     Model C99 P/N 795-6 
 
    2. Maximum allowable airspeed indicator 
     P/N 100-384043-1 - pilot's side (Model 100) 
     P/N 100-384043-5 - pilot's side (Model A100) 
     P/N 100-384043-13 - pilot's side (Model A100A) 
     P/N 100-384043-15 - pilot's side (Model B100) 
 
NOTE 1. Current weight and balance report including list of equipment included in basic empty weight, and loading 
instructions when necessary must be provided for each aircraft at the time of original certification. 
  
  a. The basic empty weight and corresponding center of gravity must include unusable fuel of 18 lb. at 
(+165) for Models A99, A99A, 20 lb. at (+169) for Models 99, 99A and 100, 28 lb. at (+173) for 
Models A100 and A100A, and 35 lb. at (+163) for Models B99 and C99. 
 
  b. The basic empty weight and corresponding center of gravity must include oil of 56 lb. at (+131) for 
Models 99, 99A, A99, A99A, B99, C99, 100, A100 and A100A. 
 
  c. The basic empty weight and corresponding center of gravity must include oil of 42 lb. at (+107) for 
Model B100. 
 
  d. The basic empty weight and corresponding center of gravity must include unusable fuel of 40 lb. at 
(+171) for Model B100. 
 
NOTE 2. All placards required in the approved Airplane Flight Manual (AFM) must be installed in the appropriate 
location. 
 
NOTE 3. Mandatory retirement time for all fuselage structural components for Models 100, A100 (U-21F), A100A and 
B100 is 20,000 hours’ time in service.  However, the Fuselage Life may be unlimited if the airplane is 
maintained and inspected at the required intervals specified in Chapter 5 (or Chapter 4 or Airworthiness 
Limitations Section, as appropriate) of the Airplane’s Maintenance Manual. 
 
  Mandatory retirement time for Models 99, 99A, A99A and B99 wing center section lower forward spar cap 
and both right and left outer panel lower forward spar caps including wing attachment fittings is as specified 
in the applicable Airworthiness Directive, or for airplanes having complied with Beechcraft Service 
Instruction 0986, the FAA Approved AFM.  Mandatory retirement times for all Model C99 structural 
components are contained in the Pilot's Operating Handbook and FAA Approved AFM (P/N 99-590030-3) 
Limitations Section.  These limitations may not be changed without FAA Engineering approval. 
 
Mandatory replacement time for Model 100, A100 and B100; serials B-1 and on, BE-1 and on all wing 
attach bolts and nuts is 15 years or 15, 000 hours, whichever occurs first; subsequent replacement times are 
the same as initial intervals as noted.

A14CE Page 17 of 17 Rev. 41 
Data Pertinent to All Models 
 
NOTE 4. The maximum propeller shaft overspeed limit for Models 99, 99A, 99A(FACH), A99, B99 and C99 is 110 
percent of all ratings and may be employed for sustained periods in emergencies.  100 percent propeller shaft 
speed is defined as 2200 rpm and is the normal steady state operating limit.  Gas generator speeds up to 102.7 
percent are permissible for 10 seconds and to 101.6 percent for unlimited periods subject to applicable 
temperature and other limits.  100 percent gas generator speed is defined as 37,500 rpm. 
 
  The maximum propeller shaft overspeed limit for Model 100, A100, and A100A is 110 percent of all ratings 
and may be employed for sustained periods in emergencies.  100 percent propeller shaft speed is defined as 
2200 rpm and is the normal steady state operating limit.  Gas generator speeds up to 102.6 percent are 
permissible for 10 seconds and to 101.5 percent for unlimited periods subject to applicable temperature and 
other limits.  100 percent gas generator speed is defined as 37,500 rpm. 
 
  For Model B100 only.  The maximum allowable propeller shaft speeds are 2100 rpm. 105 percent for a 
transient period not to exceed 5 seconds and 2020 rpm. 101  percent for 5 minutes.  Normal propeller shaft 
speed is 2000 rpm. 100 percent turbine speed is defined as 41,730 rpm. 
 
NOTE 5. Flight idle propeller low pitch stop is set so that at 2000 rpm, torque shall be an indicated 600 +60 ft.-lb. 
corrected for sea level standard day.  Secondary flight idle stop shall be 210 +40 propeller rpm higher than 
flight idle stop with a gas generator speed of 70 percent (Models 99, 99A, 100, 99A(FACH), A99, A99A and 
B99). 
 
  Flight idle propeller low pitch stop is set so that at 2000 rpm torque shall be an indicated 600 +40 ft.-lb. 
corrected for sea level standard day (Model C99). 
 
  Flight propeller low pitch stop is set so that at 2000 rpm torque shall be an indicated 660 +60 ft.-lb. corrected 
for sea level standard day.  Secondary flight and ground low pitch stop shall set so that at 2000 rpm torque 
shall be an indicated 440 +60 ft.-lb. corrected for sea level standard day (Models A100 and A100A). 
 
NOTE 6. Prior to civil certification, Model 99A(FACH) airplanes, S/N U-137 through U-145, which have been 
operated by the Chilean Air Force, must be modified per Beech Dwg. 99-002010. 
 
  Model 99, S/N U-36, U-80 through U-145 and U-147 are eligible for installation of PT6A-27 engines at the 
Beech factory and when so modified must be identified as Model 99A. 
 
  Model 99A airplanes may be modified to the A99A configuration by field or factory incorporation of Beech 
Kit 99-5008-1. 
 
  Model 99 airplanes may be modified to the A99 configuration by field or factory incorporation of Beech Kit 
99-5008. 
 
NOTE 7. Emergency use of MIL-G-5572 fuel (Models 99, 99A, A99, A99A, B99, C99, 100, A100, A100A): 
 
  Grades 80/87, 91/98, 100/130 and 115/145 are permitted for a total time period not to exceed 150 hours 
during any overhaul period.  It is not necessary to purge the unused fuel from the system when switching fuel 
types. 
 
  Emergency use of MIL-G-5572D fuel (Model B100): 
 
  Use of MIL-G-5572D, 80/87 only, aviation gasoline permitted not to exceed 1,000 gallons per engine for 
each 100 hours of engine operation.  Log book entry required.  Icing inhibitor MIL -I-2768E fuel additive 
approved not to exceed 0.15 percent by volume. 
 
NOTE 8. PT6A-27 and -28 engines may be intermixed on the 99, 99A, B99, and A99A.  PT6A-28 engine should be 
modified with the -27 rear scavenge oil tee and hose. 
 
NOTE 9. Model 99 and 99A aircraft may increase their gross weight to 10,900 pounds and increase their performance 
limitations in accordance with FAA AFM 99-590019-13 when modified per Beech Kits 99-5014-1 or 95-
5014-3.  When modified, the limitations in Section VI of the TCDS appropriate to Model B99 will apply. 
 
NOTE 10. The two (2) propeller models used on the Model C99 differ only in the manner in which the feather angle is 
adjusted.  The HC-B3TN-3B propeller has an internal feather adjustment and must be partially disassembled 
to reset the feather angle.  The HC-B3TN-3M hub has an external adjustment feature and need not be 
disassembled to reset the feather angle. 
 
 
---- END ----
```

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- [AD 92-15-01](https://openairdocs.org/ad/92-15-01): Truss-To-Firewall Bolts · Textron 100, 200, 200C and 40 more. Effective Aug 21, 1992
- [AD 90-15-18](https://openairdocs.org/ad/90-15-18): Vertical Stabilizer Main Spar · Textron 99, 99A, A99A and 1 more. Effective Sep 11, 1990
- [AD 90-12-07](https://openairdocs.org/ad/90-12-07): Wing Attach Bolts and Nuts · Textron 99, 99A, 99A (FACH) and 4 more. Effective Jul 2, 1990
- [AD 90-08-17](https://openairdocs.org/ad/90-08-17): Fuselage Moisture Drain System · Textron 100, 200, 200C and 32 more. Effective May 7, 1990
- [AD 89-25-10](https://openairdocs.org/ad/89-25-10): Wing Main Spar Inspection · Textron 100, 65-90, 65-A90 and 10 more. Effective Jan 4, 1990
- [AD 88-04-07](https://openairdocs.org/ad/88-04-07): Wing Spar Nuts Inspection · Textron 100, 65, 65-80 and 18 more. Effective Apr 18, 1988
- [AD 87-03-06 R1](https://openairdocs.org/ad/87-03-06-R1): Elevator Hinge Attachment · Textron 100, 99, 99A and 5 more. Effective Mar 12, 1987
- [AD 86-24-09](https://openairdocs.org/ad/86-24-09): POH/AFM Appendix-Icing · Textron B100. Effective Dec 15, 1986
- [AD 85-22-05](https://openairdocs.org/ad/85-22-05): Nuts and Bolts Replacement · Textron 100, 200, 200C and 60 more. Effective Nov 12, 1985
- [AD 85-01-01](https://openairdocs.org/ad/85-01-01): Acrylic Windows · Textron 100, 65-88, 65-90 and 4 more. Effective Feb 6, 1985
- [AD 69-24-02 R3](https://openairdocs.org/ad/69-24-02-R3): Maximum Speed · Textron 99, 99A, 99A (FACH) and 4 more. Effective Apr 11, 1983
- [AD 72-10-04 R2](https://openairdocs.org/ad/72-10-04-R2): Landing Gear System · Textron 99, 99A, A99 and 2 more. Effective May 13, 1982
- [AD 81-18-08 R3](https://openairdocs.org/ad/81-18-08-R3): Revised AFM · Textron 99, 99A, A99 and 2 more. Effective Feb 16, 1982
- [AD 81-23-01 R1](https://openairdocs.org/ad/81-23-01-R1): Beech Kit or Supplemental Type Certificate · Textron 100, 65, 65-88 and 20 more. Effective Jan 4, 1982
- [AD 80-09-03 R1](https://openairdocs.org/ad/80-09-03-R1): Placard -Oxygen · Textron 100, 200, 200C and 9 more. Effective Jun 11, 1980
- [AD 80-07-05](https://openairdocs.org/ad/80-07-05): Bolt and Nut, Wing Section · Textron 200, 200C, 200T and 10 more. Effective Apr 3, 1980
- [AD 79-01-01](https://openairdocs.org/ad/79-01-01): Screws in Control System · Textron 100, 200, 35-B33 and 34 more. Effective Jan 8, 1979
- [AD 78-22-05](https://openairdocs.org/ad/78-22-05): Elevator Control Push Rods · Textron 100, 50, 65 and 31 more. Effective Nov 6, 1978
- [AD 78-20-12](https://openairdocs.org/ad/78-20-12): Aircraft Tires · Cessna 336, 337, T337B and 15 more. Effective Oct 5, 1978
- [AD 78-05-06](https://openairdocs.org/ad/78-05-06): Flexible Fuel Cells · Cessna 180, 182, 185 and 98 more. Effective Jun 30, 1978
- [AD 77-18-04](https://openairdocs.org/ad/77-18-04): Cabin Pressurization · Textron 200, 200T, A100 and 3 more. Effective Sep 12, 1977
- [AD 76-22-02](https://openairdocs.org/ad/76-22-02): 'Y' Type Shoulder Harness · Textron 200, 58, 58A and 14 more. Effective Jun 2, 1977

All 69: https://openairdocs.org/tcds/A14CE/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Beech B100](https://openairdocs.org/model/beech-b100): 58 aircraft (registry code 1152919)
- [Beech C-99](https://openairdocs.org/model/beech-c-99): 54 aircraft (registry code 1154006)
- [Beech 99](https://openairdocs.org/model/beech-99): 23 aircraft (registry code 1154002)
- [Beech A100](https://openairdocs.org/model/beech-a100): 15 aircraft (registry code 1152915)
- [Beech 100](https://openairdocs.org/model/beech-100): 14 aircraft (registry code 1152916)
- [Beech 99A](https://openairdocs.org/model/beech-99a): 11 aircraft (registry code 1154003)
- [Beech B-99](https://openairdocs.org/model/beech-b-99): 6 aircraft (registry code 1154004)
- [Beech A99](https://openairdocs.org/model/beech-a99): 1 aircraft (registry code 1153802)
- [Beech A100C](https://openairdocs.org/model/beech-a100c): 0 aircraft (registry code 1152917)

## STCs approved under this data sheet (287, first 50)

- [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 SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position  Light System, and applicable associated power supplies. Whelen Aerospace Technologies
- [STC SA02133SE](https://openairdocs.org/stc/SA02133SE): Installation of a Luma Technologies LT-4500 Series Integrated Light\Emitting Diode (LED) Display Panel and LT-3500 LED light modules. Luma Technologies LLC
- [STC SA12345IB](https://openairdocs.org/stc/SA12345IB): Replacement of the Halon Type 1211 portable fire extinguisher with the Halotron BrX portable fire extinguisher. Cessna Duesseldorf Citation Service Center GmbH
- [STC SA12202IB](https://openairdocs.org/stc/SA12202IB): Installation of Garmin GWX Weather Radar System. Maxcraft Avionics Ltd.
- [STC SA2735CE](https://openairdocs.org/stc/SA2735CE): Installation of external lower fuselage cargo compartment.. Metrea Special Aerospace ISR Inc.
- [STC SA00185LA](https://openairdocs.org/stc/SA00185LA): Installation of Alternate Main Landing Gear Tires, Michelin P/N 026-335-0.. Metrea Special Aerospace ISR Inc.
- [STC SA00929AT](https://openairdocs.org/stc/SA00929AT): Installation of a TCAS-791 traffic alert and collision avoidance system (TCAS I).. Acron Aviation Inc.
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA9210SC-D](https://openairdocs.org/stc/SA9210SC-D): Installation of the L-3 Communications Avionics Systems Infrared Imaging System (IRIS). Acron Aviation Inc.
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc.
- [STC SA04196NY](https://openairdocs.org/stc/SA04196NY): Installation of LAI Heated Windshields. Lee Aerospace Inc.
- [STC SA3683NM](https://openairdocs.org/stc/SA3683NM): Installation of exhaust stack fairings.. Raisbeck Engineering Inc.
- [STC SA3819NM](https://openairdocs.org/stc/SA3819NM): Installation of nacelle overwing stowage lockers and lower flap fairing.. Raisbeck Engineering Inc.
- [STC SA4952NM](https://openairdocs.org/stc/SA4952NM): Installation of main landing gear door system for high flotation gear equipped aircraft.. Raisbeck Engineering Inc.
- [STC SA5661NM](https://openairdocs.org/stc/SA5661NM): Installation of turbofan propellers.. Raisbeck Engineering Inc.
- [STC SA00120IB](https://openairdocs.org/stc/SA00120IB): Installation of the Universal Kapture Cockpit Voice Recorder (CVR) with Recorder Independent Power Supply (RIPS). Avmax Aviation Services Inc.
- [STC SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics
- [STC SA00741WI](https://openairdocs.org/stc/SA00741WI): Installation of the Concorde RG-380E/K series VRSLA batteries in airplanes listed on the attached FAA approved Model List (AML). Aero-Mach Wilco LLC
- [STC SA1061GL](https://openairdocs.org/stc/SA1061GL): Replace existing nose wheel with Cleveland nose wheel P/N 40-204.. KAMAN Corporation Aircraft Wheel and Brake LLC
- [STC SA1509GL](https://openairdocs.org/stc/SA1509GL): Installation of Cleveland MAIN wheels and BRAKES. KAMAN Corporation Aircraft Wheel and Brake LLC
- [STC SA646GL](https://openairdocs.org/stc/SA646GL): Installation of Cleveland wheel and brake conversion kit 199-110.. KAMAN Corporation Aircraft Wheel and Brake LLC
- [STC SA00415WI](https://openairdocs.org/stc/SA00415WI): Installation of a baggage door.. Avcon Industries Inc
- [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc.
- [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". Genesys Aerosystems Inc.
- [STC SA02547AK](https://openairdocs.org/stc/SA02547AK): Limit the maximum number of passenger seats to 9. Lake Clark Air Inc.
- [STC SA6079NM](https://openairdocs.org/stc/SA6079NM): Installation of forward facing two passenger seat.. Meta Special Aerospace Air Operation Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA03556NY](https://openairdocs.org/stc/SA03556NY): Installation of a Flak Pack Ice Shield System. Avrotechnik Aviation Services Ltd.
- [STC SA5188NM](https://openairdocs.org/stc/SA5188NM): Installation of an AV557D Cockpit Voice Recorder. Honeywell International Inc
- [STC SA00776DE](https://openairdocs.org/stc/SA00776DE): Installation of 9 Passenger or Less Limitation configuration. Cert Works LLC
- [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King)
- [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC ST01930LA](https://openairdocs.org/stc/ST01930LA): Installation of Sandel Avionics SN4500 Electronic Horizontal Situation Indicator (EHSI). Sandel Avionics LLC
- [STC SA04634NY](https://openairdocs.org/stc/SA04634NY): Modification of the Brake Master Cylinder. Marsh Brothers Aviation Inc
- [STC SA04633NY](https://openairdocs.org/stc/SA04633NY): Installation of MT-Propeller Entwicklung GmbH model MTV-27-1-E-C-F-R(G)/CFR210-58( )
or /CFR224-55( ). MT- Propeller Entwicklung GmbH
- [STC SA02075SE](https://openairdocs.org/stc/SA02075SE): Installation of a Mid-Continent MD835( ) Lithium Ion Battery. Mid-Continent Instrument Co. Inc.
- [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems
- [STC SA04062NY](https://openairdocs.org/stc/SA04062NY): Installation of Garmin G600 Avionics System. airplus engineering GmbH
- [STC SA01748WI](https://openairdocs.org/stc/SA01748WI): Installation of Cabin LED Downwash Lighting. PWI Inc.
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS

All 287: https://openairdocs.org/tcds/A14CE/stcs.md

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