TCDS IM.A.277 Issue 05, .29 August 2013 Page 1 of 27 European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET Beech Models:- B200, B200C, B200GT, B200CGT, B300 and B300C (King Air) Type Certificate Holder: BEECHCRAFT CORPORATION 10511 East Central Wichita, KS 67206 USA Manufacturer: BEECHCRAFT CORPORATION 10511 East Central Wichita, KS 67206 USA For models: B200 B200C B200GT B200CGT B300 B300C Issue 5: TCDS IM.A.277 Issue 05, . 29 August 2013 Page 2 of 27 CONTENT SECTION 1: GENERAL Model B200, B200C, B200GT, B200CGT, B300, B300C, (King Air) I. II. III. IV. V. VI. General Certification Basis Technical Characteristics and Operational Limitations Operating and Service Instructions Notes Type Certificate Holder Record CHANGE RECORD Issue 1 Issue 2 Issue 3 Issue 4 Issue 5 Initial issue Models B200, B200C, B200GT B200CGT, B300, and B300C General update and correction of mistakes. Approval of B200/B200C for MTOW 14,000 lbs Restricted Category. General update and correction. B300/B300C Notes 15, 16, and 17 corrected for Typos. SECTION 1: GENERAL Model B200, B200C, B200GT, B200CGT, B300, B300C, (King Air) Type Design Data Sheet No.: EASA.IM.A.277 a) Model: Issue 5 B200, B200C, B200GT B200CGT, B300, and B300C N/A FAR-23 Normal Category Hawker Beechcraft Corporation 9709 E. Central P.O. Box 85 Wichita, KS 67201-0085 USA Hawker Beechcraft Corporation 9709 East Central P. O. Box 85 Wichita, KS 67201-0085 June 1981 - UK, S/N BB-878 (B200, B200C) 16 February 2007 (B200GT, B200CGT) April 1990 – Germany, S/N FL-7 (B300, B300C) b) Variant: 1. 2. Airworthiness Category: Type Certificate Holder: 3. Manufacturer 4. EASA Certificate Application Date: 5. FAA Type Certificate Date: 13 February 1981 (B200, B200C) 1325(e) as amended by Amendment 23-20 (B200 Series only). S/N BB-878 (B200. S/N FL-7 (B300.951(c) and FAR 23.143(a). and FAR 25.173(a) as amended by Amendment 23-14. FAR 23. Amendment 1 dated December 18. and Amendment 2 dated January 12. B200C) 14 December 2007 (B200GT. B300C Accepted under EU Regulation 1702/2003 Model B200GT.1305(n).000 feet). B300C) II.1545(a) as amended by Amendment 23-23 and FAR 23. Amendment 23-11.145(d). 23. effective February 1. FAA Special Conditions 23-47-CE-5 issued October 30. EASA Type Certificate Issue Date: (B200GT. FAR 23. 29 August 2013 Page 3 of 27 16 December 2007 12 December 1989 07 September 1990 6.161(c)(3). 4.UK. 1979.153.A. B200CGT) (B300) (B300C) June 1981 .831(d) through Amendment 25-41 (For all B200 series aircraft approved for 35. 3. (Reserved) (Reserved) Certification Basis The EASA Aircraft Type Certification standard includes that of FAA TC A24CE. 23. only). 1965. and 23. 23.1419 of FAR Part 25 as amended to December 31. 1973. FAR Part 23.TCDS IM.277 Issue 05.1529 as amended by Amendment 23-26. based on individual EU member state acceptance or certification of this standard prior to 28 September 2003. as amended by 23-1 through 23-9. B200CGT) April 1990 – Germany.997(d) as amended by Amendment 23-15 (A200CT and B200 series. FAR Paragraphs 25. . B200C Accepted under EU Regulation 1702/2003 Model B300. 1972. B200CGT Application to EASA: 16 February 2006 2. FAR Paragraphs 23. Certification Basis 1.929 and 25. 1972. Reference Date for determining Applicable requirements Model B200.175 and associated FARs 23. 23. FAR 23. Other standards conforming to TC/TCDS standards certificated by individual EU member States prior to 28 September 2003 are also acceptable. SFAR 27 through . 1305 as amended by Amendment 23-34. BB-1988 and after and for the B200C.1301. . BL152 and after.771(a)(1) as amended by Amendment 23-14. oil temperature and fuel flow. FAR 23.1311.1323(b). FAR Part 36 through Amendment 36-20. 23.1529 as amended by Amendment 23-26. 29 August 2013 Page 4 of 27 Amendment 27-4. 1993.1501 and 23. BB-1988 and after and for the B200C. Appendix A. and FAR Part 36 through Amendment 36-10. FAR 23. 1973.1547(e) as amended by Amendment 23-20. BL-152 and after. Additional requirements for the Collins IFIS Installation: 23. 23. In addition.1309.1457 as amended by Amendment 23-35.1431(b) as amended by Amendment 23-49. effective December 1.A. for direct reading digital only displays for oil pressure. B200C Serial Numbers BL-139 and after. Additional requirements for Collins Proline 21 Avionics Installation. Electronic Flight Instrument Systems shall meet the requirements of FAR 23. 23. 23. BB1444 and after. A24CE issued December 14. BB-1798. FAR 23. and 23. obtained by manufacturer under delegation option procedures.1419 when ice protection equipment is installed in accordance with the airplane equipment list. For the Models B200 and B200C: 14 CFR Part 23. Effective January 20. 23. 1994. Compliance with ice protection has been demonstrated in accordance with FAR 25.277 Issue 05.603(b) as amended by Amendment 23-23. Equivalent Level of Safety ACE-02-16 for FAR 23.1322 and 23.1305(a)(2)(3). 23.TCDS IM. FAR 135. Effective April 20. Type Certificate No.1305c(2).1321. 1971.1335 as amended through Amendment 23-41 and Special Condition 23-ACE-68. 1978 (B200 High Density Configuration. Effective Serial Numbers for the B200. BB1978. For B200 through Serial Number BB-1438 and B200C through Serial Number BL-138 FAR Part 36 through Amendment 36-10. See Note 11) Application for Type Certificate dated January 11.1549(a)(b)(c). 23.1309(a).1541(a)(a) as . FAR 23. 23. 23. For B200 Serial Numbers BB-1439. Effective at Serial Numbers for the B200. 1581(a). 23. 23. and 23.603.613 as amended by Amendment 23-45.1308(a)(b)(c)(d). 23. B200GT and B200CGT: Additional requirements for the Rockwell Collins Flight Guidance Computer FGC-3000 installation: 23. 23. 14 CFR Part 36 through Amendment 36-20.867(a)(b)(c).277 Issue 05. 23.1581(a) as amended by Amendment 23-50. 29 August 2013 Page 5 of 27 amended by Amendment 23-21.1583(h).1309(b)(c)(d)(e). 23. 23. 23.677(a). and for the B200GT. 23.301. 23. 23. 23.1351(e). 23.1365(a)(d)(e). 23. BB-1978 and BB1988 and after and for the B200C.TCDS IM. 23. For the Models B200. BL-167 and after.A. 23. 14 CFR Part 34 through Amendment 34-3. 23.321.1431(a) as amended by Amendment 23-49.337. 23. B200C.143(b) as amended by Amendment 23-49. .1357(c)(d) as amended by Amendment 23-43. BB-2018 and after.305. and for the B200CGT. 23. 23. 23. (S/N BZ-1 and after): 14 CFR Part 23-1529 as amended by Amendment 23-26.611 as amended by Amendment 23-48. 23.1311(a)(2)(3).1359(c). 23. Effective at Serial Numbers for the B200.939 as amended by Amendment 23-42. 23. 23.1329(e) as amended by Amendment 23-49. as amended by Amendment 23-57 23.1309(b)(c)(e).1585(j) as amended by Amendment 23-50.1321(e). 23.1351(a)(2)(i). 23.571.605(a) as amended by Amendment 23-23.575. For the Models B200GT and B200CGT: Additional requirements for the Models B200GT (S/N BY-1 and after) and B200CGT. Effective at Serial Numbers for the B200. 23. BL-117 and after.777(a)(b) as amended by Amendment 23-51.1351(a)(2)(i) as amended by Amendment 23-49. BZ-1 and after. and for the B200C. 23. 23.1555(a). Collins ProLine 21 Avionics is required before having the FGC-3000 installed on the airplane For B300 . 23. 23. BL-152 and after.607. 23.1357(a) as amended by Amendment 23-43.1322. 23. for use of ground minimum control speed (Vmcg) for determination of takeoff decision speed (V1). Effective January 20. 23. FAR 23.1549(a)(b)(c)(d) as amended by Amendment 23-45. 23.867(a)(b). 23. Special Conditions 23-ACE-48A effective August 13.1311(a)(b).781(b) for shape of the propeller control knob.1305(g) for use of fuel low pressure warning annunciators in lieu of the fuel pressure indicators. 23. Equivalent Safety Findings: FAR 23.TCDS IM. FAR 23.35.1305(c)(2). as amended by Amendment 36-1 through 36-15.1525.203 and 23.611 as amended by Amendment 23-48. Additional requirements for Collins Proline 21 Avionics Installation.672(a)(b)(c).277 Issue 05.1321(a)(b)(c)(d)(e).677(a)(b)(c)(d). 23. FM-9. 23.1323(a)(b)(c)(e).A. FAR 23.1305 (a)(2)(3).1549(a)(b)(c)(d). apply to Electronic Flight Instrument System (EFIS) equipped airplanes. 1969. 23.1303 (a)(b)(c)(d)(e)(f). Compliance with ice protection has been demonstrated in accordance with FAR 23.1357(a)(b)(c)(d) as amended by Amendment 23-43. 1994. 1990. . FAR 23. or prior airplanes modified by Beech Kit No.205 through amendment 23-45 (S/N FN-1 and up only). and fuel flow. 23.1321(d) for the basic "T" instrument panel arrangement. 23. and Equivalent Level of Safety ACE-02-17 for FAR 23. FAR23. 23. FAR Part 36 effective December 1. FAR 23. 130-3004). 23.207(c).305(a)(b).397(a)(b). . 23. 23.1322(a)(b)(c)(d)(e). oil temperature. for direct reading only displays for oil pressure.613(a)(b)(c)(d)(e). 23. (Serials FL-111. as amended by Amendments 27-1 through 27-6 and Exemption No.1331(a)(b)(c). FAR 23 Sections 23.561(a)(b).1419 when ice protection equipment is installed in accordance with the Equipment List.607(a)(b)(c).301(a) as amended by Amendment 23-42.201.1309(a)(b)(c)(e).53(c) (1). FN-2 and after. Special Conditions 23-131SC. Does Not Apply to Proline 21 Equipped Aircraft. 5077 from compliance with Section 23. as amended by Amendments 23-1 through 23-34. Exemption 5599 from compliance with 23. 29 August 2013 Page 6 of 27 FAR Part 23 effective February 1. 23. 1965. 23. FAR 23. and 23.1457 as amended by Amendment 23. FAR 23. 1974. SFAR 27 effective February 1. 277 Issue 05. B300C Additional requirements for the Rockwell Collins Flight Guidance Computer FGC-3000 installation: 23.1583(h). 23. 23. .1351(a)(c).277. 23. 23. FAR 23. For the Models B300.A. 23. 23.867(a)(b)(c). 23. 23. 23.TCDS IM.1585(a)(j) as amended by Amendment 23-50. 23.1585(j) as amended by Amendment 23-50.1545(a)(b)(c). 23. 23.1308(a)(b)(c)(d).677(a). 23.1309(b)(c)(d)(e).1359(c). Special Conditions: Exemptions: As shown above. 29 August 2013 Page 7 of 27 23.1325(a)(b).1555(a).777(a)(b) an amended by Amendment 23-51. 23. 6. 23. FL-538 and FL-544 and after and for the B300C.1329(a)(b)(d)(e)(f)(g)(h).1365(d)(e). 23. . 23. FAR 23. FAR 23.1357(a) as amended by Amendment 23-43. 7. 23.1365(a) as amended by Amendment 23-49. None Equivalent Level of Safety Findings: None EASA Environmental Standards: ICAO Annex 16. 23. FM-15 and after.1583(h). 23.1353(h).771(a).A.337. 23. 23.574.1431(a)(b)(d)(e) as amended by Amendment 23-49. as amended by Amendment 23-57 23.143(b) as amended by Amendment 23-49.321 as amended by Amendment 23-45. B300C.1305(a)(c)(e) as amended by Amendment 2352.575 as amended by Amendment 23-48.1581(a). Additional requirements for the Collins IFIS Installation: 23. Effective at Serial Numbers for the B300.1329(e) as amended by Amendment 23-49.1581(a) as amended by Amendment 23-50. Effective at Serial Numbers for the B300 FL-748 and after and for B300C FM-50 and after. 8. Collins ProLine 21 Avionics is required before having the FGC-3000 installed on the airplane 5. 23. and after. Volume 1 see EASA Type Certificate Data Sheet Noise ref TCDSN IM. 200C.) Height 4. meters (303. 10 in. ft.) High Flotation Landing Gear: Span 16. BB-817 through BB-824. Type Design Definition: Aircraft General Assembly. King Air. retractable tricycle landing gear and T-tail. Drawing No. At low altitude and low ambient temperature the engines may produce more power at takeoff than that for which the airplane has been certificated. See Pilots Operating Handbook and FAA Approved Airplane Flight Manual. 6 in. 101-000009. 4.1496 sq.) Length 13.) Length 13. BL- . Limitations.) Height 4.) 5. Technical Characteristics and Operational Limitations MODEL B200.0% 1900 850 850 N¹ Gas Generator Speed 101. A200C) 750 (200.5% 101. latest FAA revision.52 m (14 ft. or Pratt & Whitney PT6A-42 (Turboprop) per Beech Specification BS 23319/1 (B200.61 m (54 ft. 3. or later approved revision. Description: Equipment: Dimensions: Engine Limits: *See Note 4. Ltd. 101-000007 and B200C. C) 750 (200. 6 in.36 m (43 ft. meters (303. 200C.1496 sq. 10 in. Under these conditions. A200C) 1000 750 2. 29 August 2013 Page 8 of 27 III. Model B200. P/N 101-590010479. . Propellers: 2 Hartzell HC-B3TN-3G or HC-B3TN-3N hubs with Hartzell T10178B-3R or T10178NB-3R blades for: BB-1 through BB-815. (Deg.) Wing Area 28.) Wing Area 28. Drawing No. 9 in. P/N 101-590010-479 for engine operating limits under Section II.4196 m (14 ft. ft.TCDS IM.0 sq. B200C 1. Permissible Turbine Interstage Temp. Aircraft with two wing-mounted turboprop engines.5% Prop Shaft Speed 2000* 2000* Max.A.61 m (54 ft.355 m (43 ft. Standard Landing Gear: Span 16. Engines 2 United Aircraft of Canada. King Air. 6. 6 in. B200C) Shaft Horsepower Takeoff (5 minutes) Max Continuous Starting Transient (2 seconds) Max Reverse (1 minute) 88.0 sq. the placarded torquemeter limits shall not be exceeded.277 Issue 05. Equipment list according AFM. ) No further reduction permitted. 29 August 2013 Page 9 of 27 1 through BL-29.) (Maximum) Minimum allowable for repair 2.m.TCDS IM.5 in.p. BP-64 & after. BB-1463.4° Continuous operation on the ground is prohibited between 600 and 1150 r.0 +0.39 m (94 in. BB-1444 & after except BB1463. B200 Serials BB-1193 through BB-1438. BB-1440 through BB1443.46 m (97 in. Diameter: 2. Pitch settings at: Flight idle stop See Note 5(a) Reverse -10o Feathered +86.8o B200 Serials BB-1439.277 Issue 05. BJ-1 and after or Hartzell T10178K-3R or T10178NK-3R blades for: BB-816. BL-124 through BL138.49 m (98 in.) (maximum). minimum allowable for repair: 2. and BV-1 & after 2 McCauley 3GFR34C702 hubs with McCauley 100LA-2 blades Diameter: 2. BB-825 through BB-1438.76 m (30 in. The propeller must be feathered to ground idle at rotational speeds below 600 propeller shaft r.5 in. B200C Serials BL-124 through BL-138.p.50 m (98.) (maximum). BL-30 through BL-72.: Flight idle stop See Note 5(a) Secondary flight idle stop See Note 5(b) Reverse -9˚ Feather +90˚ B200C Serials BL-73 through BL-123)(C-12F) 2 McCauley 4HFR34C754 hubs with McCauley 94LA-0 blades Diameter: 2.m.) Sta. . Pitch settings at 0.48 m (97.) (B200C Serials BL-73 No further reduction permitted through BL-123)(C-12F) Pitch settings at: Flight idle stop See Note 13(a) Ground idle stop See Note 13(b) Reverse -10. minimum allowable for repairs: 2.36 m (93 in. BU-1 and after. B200C Serials BL-139 & after and BW-1 & after 2 McCauley 4HFR34C771 hubs with McCauley 94LA-O blades .A. BB-1440 through BB-1443.) No further reduction permitted. 36 m (93. JP-8 (MIL-T83133). 8. Pitch settings at: Flight idle stop See Note 13(a) Reverse -10. The propeller must be feathered at rotational speeds below 600 propeller shaft r. minimum allowable for repair: 2.277 Issue 05.0+0.) No further reduction permitted. Minimum allowable for repairs: 2.1.B. in addition for B200 and B200C Chinese No. .5 in.) (maximum). . 8.2.A.) (maximum). Pitch settings at: Flight idle stop See Note 5(a) Secondary flight idle stop See Note 5(b) Reverse -9° Feathered +90° 7.39 m (94 in.) No further reduction permitted.5 in. JP-5 (MIL-T-5624).TCDS IM.5+.180 RPM.m.48 m (97.3o Continuous operation on the ground is prohibited between 600 and 1100 r. The propeller must be feathered at rotational speeds below 500 propeller shaft RPM.2+0. Or 2 Hartzell HC-B3TN-3G or HC-B3TN-3N hubs with Hartzell T10178B-3R or T10178NB-3R blades Diameter: 2. Fuel: JP-4.8+0. Or 2 Hartzell HC-E4N-3G hubs with Hartzell D9390SK-1R blades Diameter: 2. 29 August 2013 Page 10 of 27 Diameter: 2.p.50 m (98. Jet A-1.5o Feathered +85. (Reserved) Fluids 8. Pitch Settings at: Flight Idle Stop See Note 13(c) Reverse -11. 3 Jet Fuel.34 m (92 in.5o Continuous operation on the ground is prohibited between 500 and 1.36 m (93 in.) (maximum). 1244 or ASTM Spec D1655. See Note 29 for emergency fuels. Jet A. minimum allowable for repairs: 2.p.) No further reduction permitted.m.4o Feathered 87. and Jet B conforming to P&WC S.5 in. 3. Limitations. BV-1 and after.8 m (31. GAL. Maximum Operating Altitude: 10668 m (35.1 liters) 79.1.000 ft. P/N 101-590010-479 for airplane limit speeds under Section II.) .2 qt)) at +131 (includes 5.4 qt. BP-64 and after. and BB-44.2 liters) (730.) – Serials BB-38. 9448. BU-1 and after.5 79.000 ft.0 +204 (300. 11.S. BB42. BB-54.S CAP.Serials prior to BB-54 except BB-38. BL-1 and after. N/A Coolant: 9. BB-39.6 liters) See Note 1(a) for data on unusable fuel.71 l each engine (9.2 liters) (730.5 79. U.68 l (6 qt. 3001 lists approved brand oils.2.277 Issue 05. and after*. BB-42.TCDS IM. Fuel Auxiliary LH Auxiliary RH Main LH Main RH U. BJ-1 and after . Fuel Capacities: 9. BB-44. BB-39. Airplane Limit Speeds (KCAS) Maximum operating speed Maneuvering Flaps extended speed Approach position 14˚ 100% position 35˚ Maximum landing gear operating speed Extension Retraction Maximum landing gear extended speed 200 knots 155 knots 182 knots 164 knots 182 knots 270 knots 182 knots See Pilots Operating Handbook and FAA Approved Airplane Flight Manual. ARM 79.41 l (18. 17. . 9.6 liters) 195 193 +185 (738.) usable in each integral tank) See Note 1(c) for data on unusable oil.1 liters) 195 193 +185 (738.9 liters) (299.0 +204 (300.A. USABLE GAL. Oil: 10. 29 August 2013 Page 11 of 27 8.) total (8. Oil: Pratt & Whitney Service Bulletin No.9 liters) (299. BW-1 & after. 29 August 2013 Page 12 of 27 *And any earlier airplanes modified by Beechcraft Kits 101-5007 and 101-5008 in compliance with Beechcraft Service Instruction Number 0776-341. One pilot Max. Baggage/Cargo Compartment (Structural Limit): 185.277 Issue 05. Higher Gross weight operations may be permitted in restricted category see Notes section for details.500 lb 13. aft of the cargo door on Model B200C. 117. Limitations. 2 external screws on left side of fuselage forward of entrance door on Model B200. B200C. Datum: 16. 17. BP-64 & after.) (+325) B200 prior to BB-1091. 88. (Reserved) Leveling means: 18. The reference datum is located 482. B200C prior to BL-58 when kit 1015068-1 is installed).4 kg (550 lb.590 lb Takeoff 5669.TCDS IM.) nose (+70). BU-1 & after. pod aft (+214).) (B200 High Density Configuration. BV-1 & after.9 kg 12. Maximum Certified Weights See Pilots Operating Handbook and FAA Approved Airplane Flight Manual.9 kg 12. Operational Capacity: VFR Day and Night IFR Day and Night Icing Conditions (Normal Category) Ramp 5669. 14. Minimum Flight Crew: . 9 15.)(+325)(B200. BL-58 & after.4 kg 195 lb. See Note 11) 12.9 kg (410 lb.7 kg (350 lb. Limitations. B200C prior to BL-58) 249. BW-1 & after) B200 prior to BB-1091.0 inches) forward of the wing main (forward spar centerline. . Centre of Gravity Range See Pilots Operating Handbook and FAA Approved Airplane Flight Manual. P/N 101-590010479 for weight limits under Section II. 101-590010-479 for airplane centre of gravity under Section II. BB-1091 & after.000 ft. 158. Passenger Seating Capacity: 19. pod forward (+165).6 centimetres (190. 7620 m (25.500 lb Landing 5669.9 kg 12.9 kg (260 lb).A. King Air. BW-1 & up. . BB-894. (Deg. . B200C: BL-37 and up. B200CGT 1.) 4. See notes 23 and 24.A. PT6A52 (Turboprop) Per Beech Specification BS267046 (B200GT. See Note 11 20. Serial Numbers Eligible: MODEL B200GT. Drawing No. B200CGT). Engines 2 Pratt & Whitney Aircraft of Canada. Drawing No.0 Prop Shaft Speed 2000* 2000* 2200* 1900 Max. Wheels and Tyres: Main Landing Gear (MLG) 5. 8 ply rated B200: BB-734. retractable tricycle landing gear and T-tail. BB-793.277 Issue 05. Aircraft with two wing-mounted turboprop engines.5 Type VII x 18.) 13. BP-64 and up. latest FAA revision. 10 in. 21. King Air. BB-854 through BB-870. 8 ply rated Nose Landing Gear (NLG) 6. BB-829. BB-1315 through BB-1384. BB-874 through BB-891.0 104. Type Design Definition: Aircraft General Assembly. Description: 3.TCDS IM. BB-913 through BB-990. Shaft Horsepower N¹ Gas Generator Speed 104. Span Length Height Wing Area 16. BB1389 and up. ft. BU-1 through BU-10.5 m (14 ft.101-000068.) 2. See Note 23.0 104. P/N 101-590168-1. Model B200GT.0 800 88. Ltd.3 m (43 ft. 10 in. BB-896 through BB-911. BB-992 through BB-1313. Permissible Turbine Interstage Temp.0 sq.) aft cabin (+325) (B200 High Density Configuration. BV-1 through BV-10.) 28. Equipment list according AFM. or later approved revision. C) 820 820 1000 760 Engine Limits: Takeoff (5 minutes) Max Continuous Starting Transient (2 seconds) Max Reverse (1 minute) 850 850 *See Note 4.3 kg (510 lb.15 sq. B200CGT. 101-000069.75-10 x 22. Dimensions: 5. Equipment: 4. meters (303.6 m (54 ft. 29 August 2013 Page 13 of 27 231. 6 in. 5 (300. Oil: 18.34 m (92.6 liters) See Note 1(a) for data on unusable fuel.0 +204 (299.) usable in each integral engine tank See Note 1(c) for data on unusable oil.. 13001 lists approved brand oils. See Note 6 for emergency fuels. P/N 101-590168-1 for engine operating limits under Section II.0 in. 9.) No further reduction permitted.9 liters) 195 (738. Coolant: 9. GAL.2˚ ± .5˚ Feather 85.TCDS IM.9 liters) 79. JP-8 (MIL-T83133).36 m (93.S.) (maximum) Minimum allowable for repair 2.A. Jet A.0 in.1 liters) 79. The propeller must be feathered at rotational speeds below 500 propeller shaft RPM.2.2. USABLE GAL. (Reserved) 8.1 liters) 193 +185 (730.B. Fluids 8. .6 liters) 193 +185 (730. and Jet B conforming to P&WC S. Pitch settings at: Flight idle stop (See Note 13(c) Reverse -11.2 liters) U.68 l (6 qt. Oil: Pratt & Whitney Service Bulletin No. 1244 or ASTM Spec D1655. JP-5 (MIL-T-5624). 29 August 2013 Page 14 of 27 See Pilots Operating Handbook and FAA Approved Airplane Flight Manual. Fuel Capacities: 9. 79.277 Issue 05. 3 Jet Fuel.93 l (20 qt.1. Fuel: JP-4.) total (9. Jet A-1.5 (300.2 liters) 195 (738.180 RPM.1.8˚ ± . 6. . 8.46 l (10 qt. and Chinese No.S CAP. Fuel Auxiliary LH Auxiliary RH Main LH Main RH U.5˚ Continuous operation on the ground is prohibited between 500 and 1. Limitations.0 +204 (299. ARM 79.) per each engine)) at +131 (includes 5. 7. Propellers 2 Hartzell HC-E4N-3G hubs with Hartzell D9390SK-1R blades Diameter: 2.3. N/A 8. Operational Capacity: 10668 m (35. 15. 11. P/N 101-5901681 for weight limits under Section II.TCDS IM. The reference datum is located 482.) Serials BY-1 and after and BZ1 and after. Higher Gross weight operations may be permitted in restricted category see Notes section for details. 2 external screws on left side of fuselage forward of entrance door. Maximum Certified Weights See Pilots Operating Handbook and FAA Approved Airplane Flight Manual.590 lb Takeoff 5669. 14. Datum: 16. Limitations.277 Issue 05.A. . 29 August 2013 Page 15 of 27 10. Maximum Operating Altitude: 12. Limitations.9 kg 12.9 kg 12. VFR Day and Night IFR Day and Night Icing Conditions (Normal Category) Ramp 5710. (Reserved) 17. Limitations.000 ft.6 centimetres (190. P/N 101-590168-1 for airplane centre of gravity under Section II.500 lb 13. P/N 101-590168-1 for airplane limit speeds under Section II. Airplane Limit Speeds (KCAS) Maximum operating speed Maneuvering Flaps extended speed Approach position 14˚ 100% position 35˚ Maximum landing gear operating speed Extension Retraction Maximum landing gear extended speed 200 knots 155 knots 182 knots 164 knots 182 knots 260 knots 182 knots See Pilots Operating Handbook and FAA Approved Airplane Flight Manual. Centre of Gravity Range See Pilots Operating Handbook and FAA Approved Airplane Flight Manual.7 kg 12.500 lb Landing 5669. Leveling means: .0 inches) forward of the wing main (forward spar centerline. Engines 2 Pratt & Whitney Aircraft of Canada. B300C. Equipment: 4. Passenger Seating Capacity: One Pilot 9 20. Span Length Height Wing Area 17. Model B300. retractable tricycle landing gear and T tail.36 m (14 ft. the placarded torquemeter . 8 ply rated B200GT: BY-1 and after B200CGT: BZ-1 and after 22.87 sq. *See Note 17 for alternate P&W PT60A-67A engine installation kit.2 m (46 ft.) 27. (+325) 21. 8 in. meters (300. 29 August 2013 Page 16 of 27 18. Minimum Flight Crew: 19.5 Type VII x 18.75-10 x 22.6 m (57 ft. 4 in. Type Design Definition: Aircraft General Assembly. P/N 130-590031235. King Air. Description: 3. Dimensions: 5.) 4. Drawing No. 130-000001. 130-000000. Permissible Turbine Interstage Temp. Aircraft with two wing-mounted turboprop engines. 8 ply rated Nose Landing Gear (NLG) 6.A. C) 820 820 1000 760 *See Note 4. or later approved revision.) 14.277 Issue 05.0 sq. Wheels and Tyres: Main Landing Gear (MLG) 5. Engine Limits: Shaft Horsepower Takeoff (5 minutes) Max Continuous Starting Transient (2 seconds) Max Reverse (1 minute) 900 1650 1050 1050 N¹ Gas Generator Speed 104% 104% Prop Shaft Speed 1700* 1700* Max. Equipment list according AFM. Ltd. 11 in.TCDS IM. PT6A60A (Turboprop) Per Beech Specification BS 23433B. latest FAA revision. King Air. ft. B300C 1. Max.) 2. Under these conditions. Drawing No. Baggage/Cargo Compartment (Structural Limit): 550 lb. . At low altitude and low ambient temperature the engines may produce more power at takeoff than that for which the airplane has been certificated. Serial Numbers Eligible: MODEL B300. (Deg. P/N 130-590031-235 for engine operating limits under Section II.8 liters) (300. 3 Jet Fuel. U.9 liters) 80.5 +219. See Pilots Operating Handbook and FAA Approved Airplane Flight Manual.0 79.5 liters) (719.) (Nominal) Minimum allowable for repair 2.1 (302.00 in. USABLE GAL. or M10476NSK blades Diameter: 2. 18. and Jet B conforming to P&WC Service Bulletin 13044 or ASTM Spec D1655.2 liters) 193.68 l (6 qt.46 l (10 qts.TCDS IM.1 (302.0 190 +199 (730. each engine)) includes 5.5 +219.5˚ minimum idle speed 1050 rpm 7.8 liters) (300. Jet A. JP-5 (MIL-T-5624).) usable in each integral engine See Note 1(b) for data on unusable oil.00 in.5 liters) (719. Fuel: JP-4. Limitations. P&WC PT6 Engine Service Bulletin No. * See AFM. Propellers 2 Hartzell HC-B4MP-3C hubs with Hartzell M10476K.0 79. M10476NK. .277 Issue 05.) (no further reduction permitted) Pitch settings at: Flight idle stop (See Note 5) Reverse -14˚ ± . JP-8 (MIL-T83133). P/N 130-590031-235 for variations.5˚ Feathered +80.64 m (104.0 190 +199 (730.67 m (105.9 l (20 qt.S. Oil: b. GAL.2 liters) 80. Fuel Main LH Main RH Auxiliary LH Auxiliary RH U. Coolant: 9. 6. Oil: . (Reserved) 8. Jet A-1. 13001 lists approved brand oils. See Note 6 for emergency fuels. ARM* 193.) total (9. Fuel Capacities: a. Fluids 1.S CAP.A.9 liters) See Note 1(a) for data on unusable fuel. 29 August 2013 Page 17 of 27 limits shall not be exceeded. b. N/A 2.0˚ ± . and Chinese No. 000 lb Landing 6803.100 lb Takeoff 6803.A.9 kg 15.2 kg 15.000 lb 13. Operational Capacity: 10668 m (35. Limitations. 15. P/N 130-590031-235 for airplane limit speeds under Section II. Higher Gross weight operations may be permitted in restricted category see Notes section.9 kg 15.up to 6401 m (21.277 Issue 05.58 Mach) 184 knots 202 knots 158 knots Maneuvering Flaps extended speed Approach position 14˚ 100% position 35˚ Maximum landing gear operating speed Extension Retraction Maximum landing gear extended speed 184 knots 166 knots 184 knots See Pilots Operating Handbook and FAA Approved Airplane Flight Manual. 11.TCDS IM.000 ft) 263 knots 263 – 194 knots (0. Airplane Limit Speeds (KIAS) Maximum operating speed . P/N 130-590031-235 for airplane centre of gravity under Section II. Centre of Gravity Range See Pilots Operating Handbook and FAA Approved Airplane Flight Manual. 29 August 2013 Page 18 of 27 10.000ft up to 35.5 inches) forward of the center of the nose jack point. The reference datum is located 212 centimetres (83.) pressure altitude VFR Day and Night IFR Day and Night Icing Conditions (Commuter Category) Ramp 6849. Limitations. Note 15 and 16 for details. Limitations. P/N 130-590031235 for weight limits under Section II.000 ft.000 ft. Maximum Certified Weights See Pilots Operating Handbook and FAA Approved Airplane Flight Manual.) Maximum operating speed . . Maximum Operating Altitude: 12. Datum: .6401 m up to 10668 m (21. 14. Leveling means: 18. and Printed Circuit Board Manual) King Air 300 Series Interactive Maintenance Library. Component Maintenance Manual. 1 Pilot 17 (including pilot and co-pilot). 22. P/N 101-590010479.277 Issue 05.3 kg (510 lbs. or later approved version. P/N IML-300 (Includes Wiring Diagram Manual. or later approved version. and FL-382. FM-1 and up (Model B300C) See Note 10. King Air B200. B300C POH/AFM. 10 ply rated Nose Landing Gear (NLG) 6. or later approved version. (Reserved) 17. FM-1 through FM-11 only) 21. Operation and Service Instructions Airplane Flight Manual (AFM) King Air B200. Structural Repair Manual.5 kg (550 lb. Airplane Maintenance Manual King Air 200 Series Interactive Maintenance Library. P/N 101590168-1.TCDS IM. . King Air B200GT.) (+359). Maintenance Manual. Baggage/Cargo Compartment (Structural Limit): 249. FN-1 and up (Model B300C) See Note 10.75-8 x 19.) with foldup seats installed (S/N FL-1 through FL380. 231. Illustrated Parts Catalogue. Illustrated Parts Catalogue. Wheels and Tyres: Main Landing Gear (MLG) 6. 8 ply rated FL-1 and up (Model B300) See Note 10. P/N 101-590010425. Structural Repair Manual. Notes Data Pertinent to All Model 200 Series . B200C POH/AFM. Minimum Flight Crew: 19. and Printed Circuit Board Manual) V. 29 August 2013 Page 19 of 27 16. or later approved version. Max. Maintenance Manual.A. 20. King Air B300. Serial Numbers Eligible: IV. P/N IML-200 (Includes Wiring Diagram Manual.75-10 x 22. Passenger Seating Capacity: 2 external screws on left side of fuselage forward of entrance door. B200CGT POH/AFM. Component Maintenance Manual. P/N 130-590031235. B200C POH/AFM. Restricted Category Maximum Pilot’s Operating Handbook . Left intentionally blank. at (+170 in. B200C). loading information and a list of equipment included in empty weight must be provided for each airplane at the time of original certification. A 100 percent propeller shaft speed is defined as 2000 r. NOTE 5. being undrainable.277 Issue 05.m.-lb. (b) Secondary flight idle stop shall be 210 +40 propeller r. B200C. (a) Basic empty weight includes unusable fuel of 44 lb. B200T. 29 August 2013 Page 20 of 27 NOTE 1. being unusable. (a) Flight idle propeller low pitch stop is set so that at 1800 r.p. (Models B200. A 100 percent gas generator speed is defined as 37. NOTE 3.m. P/N 101-590010-453 for Models B200. 100/130.p. Current weight and balance data.m. and 115/145 are permitted for a total time period not to exceed 150 hours time between engine overhauls. The following models have been delivered and are eligible for multiple airworthiness certification per FAR 21. being undrainable. Mandatory retirement times for all structural components are contained in the FAA Approved Airworthiness Limitations Manual.A. NOTE 10.p. at (+131 in. Emergency use of MIL-G-5572: Grades 80/87.) with 38 lb. there shall be an indicated 800 +60 ft. Left intentionally blank.p.p. Left intentionally blank. at (+163 in. .5 percent for unlimited periods subject to applicable temperature and other limits. NOTE 9. 91/98. (b) Basic empty weight includes unusable fuel of 37 lb.) of all ratings. NOTE 6. NOTE 4. and is the normal steady state operating limit. It is not necessary to purge the unused fuel from the system when switching fuel types. FAR’s Inappropriate for Restricted Category NOTE 2.TCDS IM. The maximum propeller shaft overspeed limit is 110 percent (2200 r.) with 10 lb.m. torque corrected to sea level standard day. NOTE 7. higher than flight idle stop with a gas generator speed of 70 percent (for airplanes not complying with SI 0808-247 only).6 percent are permissible for 10 seconds and to 101. Gas generator speeds up to 102. (c) Basic empty weight includes engine oil of 62 lb.187 in Normal and Restricted Category at indicated gross weight and other limitations specified by the applicable Airplane Flight Manual (AFM) or Pilot's Operating Handbook (POH) for any special purpose that is specified by an FAA Approved Supplement to the applicable AFM or POH. All placards required in the approved Airplane Flight Manual must be installed in the appropriate location. B200GT and B200CGT.500 r.5 lb.) with 10. B200CT.m. NOTE 8. m. (a) Flight idle propeller low pitch stop is set so that at 1800 r.1 is inappropriate (C-12F). .000 lbs MTOW must be EASA approved and applicable to the aircraft Serial.800 RPM there shall be an indicated 522+20 ft.500 lbs MTOW the aircraft is only eligible for a Restricted Category C of A.000 pounds gross weight providing the pertinent limitations. Based on the type of mission being performed. This increased gross weight of 14.A. 29 August 2013 Page 21 of 27 Purpose Certification Gross Wt. the Flight Manual Supplement. NOTE 14. are eligible for operation as noted below: Model B200 Manufactured Config. 101-590010-241 surveying B200C Aerial 23.lb.TCDS IM. (b) Ground idle propeller low pitch stop is set so that at 1800 r. 101-590010-317 surveying *See the applicable section of this data sheet for Normal Category gross weight. lb. Left intentionally blank. however:-. torque corrected to sea level standard day.775 12.000 lbs.277 Issue 05. NOTE 13. 101-590010-257 inspection B200 Aerial 23. . when modified to the applicable Beech Modification Drawing.000 lbs. When Operating above 12.1 14. Left intentionally blank. Airworthiness Limitations Supplement and Structural Inspection and Repair Manual Supplement to operate at 14. there shall be an indicated 740 +40 ft. NOTE 16. FAR 23.lb. as specified by the FAA Approved Airplane Flight Manual Supplement 101-590010-261.m.1 14. are followed and the aircraft is marked to comply with FAR Part 45. torque corrected to sea level standard day. 23. Export Eligible Operation Export to the United Kingdom Export to the United Kingdom Export to France Beech Mod 101-005004 Model B200C B200C Export 101-005020 B200.1. NOTE 11. torque corrected to sea level standard day.1 14.000 lbs.500 lbs. The following models. Left intentionally blank.p. (c) Flight Idle Propeller Low Pitch Stop is set so that at 1. B200C (C-12F) Serials BL-99 through BL-104 are certified in only the restricted category for aerial surveying at 14.* Supplement Aerial 23. 101-590010-261 surveying B200 Flight 23. B200C Export 101-005006 or 101-005003 NOTE 12. there shall be an indicated 330 +40 ft.000 lbs has been EASA approved. NOTE 15.p. Left intentionally blank. BB-1834. NOTE 22. NOTE 26: .177(a)(2) are inappropriate. Company name change effective 4/15/96. See Summit Aviation AFM Supplement No. The following serial numbers are manufactured under the name of Raytheon Aircraft Company: B200: BB-1532 through BB-1977. The Model B200. Left intentionally blank. RVSM capability per STC ST01278SE for serials BB-1769. RVSM capability per STC ST01798SE for serials BB-2001 through BB-2018. FM12 and after. Serial BL-65. BB-1386. NOTE 25. 23. FL-381. NOTE 23. NOTE 21. FL-383 and after. Serial BB-1114. for flight hour definition. BB-1388 The following serials are not eligible for FAA or EASA certification for civil registration: (B200C) BV-11 and BV-12 (UC-12M with military designation RC-12M) (B200C) BU-11 and BU-12 (UC-12F with military designation RC-12F) RVSM capability per STC ST01070SE for serials BB-2 through BB-1768.775(e). cease to be eligible for return to Normal Category. RVSM Group approval per STC SA01798SE for serials FL-329. at 14. Appendix G. as specified by Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement 101-590010-235 are followed and the aircraft is marked to comply with FAR Part 45. . BY-45 through BY-170. BL-148 through BL-151. NOTE 18. NOTE 20. and 23. BB-1843 through BB-2000. BL-1 through BL-147. 29 August 2013 Page 22 of 27 NOTE 17. providing the pertinent limitations.A. The following serial numbers were delivered to the Government of Israel and are not eligible for FAA or EASA certification or civil registration: B200 serials BB1385.277 Issue 05. These STCs approve the noted aircraft to 14 CFR Part 91. Once certificated in the Restricted Category. Appendix G. BL152 through BL-170. BB-1835. This STC approves the noted aircraft to 14 CFR Part 91. B200C: BL-141 through BL-151. the Model B200. NOTE 24. 1 dated September 11. Final certification for RVSM operations must be obtained by the operator form the local Competent Authority Flight Standards Office (FSO).000 pounds gross weight. and Model B200C. Final certification for RVSM operations must be obtained by the operator from the local Competent Authority Flight Standards Office (FSO). Left intentionally blank. Left intentionally blank.1. BB1770 through BB-1833.TCDS IM.177(a)(1). 1986. FAR 23. NOTE 19. Left intentionally blank. 23. Serials BB-1204 and BB-1205 are certified in the Restricted Category only for aerial surveillance. BB-1387. Serial BB-1206 is certified in the Restricted Category only for flight inspection. FAR 23.m. (a) Basic empty weight includes unusable fuel of 52 lb. being undrainable. 23. at (+182.p. See also Note 10 above. One hundred percent gas generator speed is defined as 37. NOTE 3.277 Issue 05.p. as specified by Pilot’s Operating Handbook and EASA/FAA approved Flight Manual Supplement 101-590010-413 are followed and the aircraft is marked to comply with FAR Part 45. and is the normal steady state operating limit. providing the pertinent limitations.1301(a) [Amdt.) of all ratings.p. The following serial numbers are manufactured under the name of Hawker Beechcraft Corporation: BB-1976 and after.A. (b) Basic empty weight includes engine oil of 57 lb.TCDS IM. at 14. Current weight and balance data. 29 August 2013 Page 23 of 27 For RVSM aspects ony.4 in. (P/N 130-590031-1 or 130-590031-71 or 130-590031-181) must be installed in the appropriate locations. the Model B200 series Pitot-Static system meets the requirements of 14 CFR Part 23. Mandatory retirement times for all structural components are contained in the EASA/FAA Approved Airworthiness Limitation Manual.500 r. .) with 10 lb. being unusable. NOTE 4. NOTE 27: The Model B200 Serials BB-1733 and BB-1744 are certified in the Restricted Category only for aerial surveillance.177(a)(1).000 pounds gross weight. One hundred percent propeller shaft speed is defined as 1700 r. loading information. and a list of equipment included in empty weight must be provided for each airplane at the time of original certification.7 lb. All placards required in the Pilot's Operating Handbook. The maximum propeller shaft overspeed limit is 110 percent (1870 r.1.m.) with 33.775(e). P/N 130-590031-211 (For FL-1 and up and FM-1 and up) and Chapter 4 of the Beechcraft B300 Maintenance Manual Supplement 130-590031-67 (for FN-1 and up).4 in. 23-20]. Gas generator speeds up to 104 percent are for unlimited periods subject to applicable temperature and other limits. Company name change effective 3-26-07.177(a)(2) are inappropriate. NOTE 2. 23. and 23. . at (+132.m. These limitations may not be changed without EASA Approval. Emergency Engine Fuels for the Models B200GT and B200CGT (see Limitations Section of the POH/AFM for Limitations) 80 Red (Formerly 80//87 100LL Blue 100 Green NOTE 28: NOTE 29: Data Pertinent to All Model B300 and B300C Series NOTE 1. -9. Appendix G.TCDS IM. . or 100LL aviation gasoline per ASTM D910. or Grades 80/87. 15. -6. Model Purpose B300C Photographic Contact Hawker Beechcraft Corporation as necessary to obtain availability information concerning the drawings and kits. Flight idle propeller low pitch stop is set so that at 1500 r. RVSM Group Approval per STC SA01798SE for serials FL-329. Alternate use of aviation gasoline: Use of Grades 80.000 130-590031-65 23. FAR's Inappropriate for Restricted Maximum Pilot's Operating Category Certification Gross Wt. NOTE 7.1545(b) NOTE 6. is not less than 1050 r.187 in Commuter and Restricted Category at indicated gross weight and other limitations specified by the applicable Airplane Flight Manual (AFM) or Pilot's Operating Handbook (POH) for any special purpose that is specified by an EASA/FAA Approved Supplement to the applicable AFM or POH.p.277 Issue 05. or 11.A. 100. B300C: FM-9 and up. standard day conditions. FL-383 through FL-839. Model B300 B300/B300C Beech Drawing 130-005002 130-005005 Company name change effective 4/15/96. Handbook Supplement 23. FN-2 and up. -5.p. The 8 cabin seats in the double club cabin arrangement must be of the narrow back configuration part numbers 130-530074-1.775(e). FM-12 through FM-53. -4. These STCs approve the noted aircraft to 14 CFR Part 91. NOTE 9. NOTE 8. FM-1 through FM-11. 23. -7. It is not necessary to purge the unused fuel from the system when switching fuel types. The Models B300/B300C are eligible for EU C of A issuance when modified to the following drawings: EU Approval by United Kingdom France NOTE 10. 29 August 2013 Page 24 of 27 NOTE 5. Final certification for RVSM operations must be obtained by the operator from the local Competent Authority Flight Standards Office (FSO). 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. 91/96. The following models have been delivered and are eligible for multiple airworthiness certification per FAR 21. The following serial numbers are manufactured under the name of Raytheon Aircraft Company: B300: FL-137 through FL-423. -2. NOTE 11: .m.1. -3. RVSM Group Approval per STC ST01070SE for serials FL-1 through FL-328. the airplane must be equipped with the following: 1. FL-381.p. Ground idle low pitch stop is set so that at 62 to 64 percent N1 prop r. the engine torque is 36 percent for sea level. which are referenced by this publication. 100/130. FL330 through FL-380 and FL-382. or -12. With passenger seating of 10 or more.m.m. 23. ref EASA approval EASA. (718 kg) (2 tanks.205. . 23. FM-17. P/N 130-590031-245 . Airplanes that also have the extended range fuel tanks installed are to use Pilot’s Operating Handbook.0) at 16 500 lb (+191. FM-18 and FM-48. 118 gal.C.IM.S.) 775 U.277 Issue 05.01656. FM-16. 130-590031-255. The areas of change from a standard B300 and B300C are listed below: Design Weights Max Ramp Weight Max Takeoff Weight Max Landing Weight Max Zero Weight 16 600 lb (7 530 kg) 16 500 lb (7 484 kg) 15 675 lb (7 110 kg) 13 000 lb (5 897 kg) C.S. and 23.7 lb/ U. each) 236 U. NOTE 14: Re-evaluation of structure and fatigue will be required for serial numbers FM-14. gallon = 6. For these aircraft operated with wing hard points that have been removed from the Civil Register the use of these hard points and their effect on airframe life has to be agreed and approved by EASA before they can return to civil operation. and FL-526 and after.50.A. The following serial numbers are manufactured under the name of Hawker Beechcraft Corporation: FL-424. Range (Landing Gear Extended) (+203. NOTE 15: 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 Pilot’s Operating Handbook and EASA/FAA Approved Airplane Flight Manual (POH/AFM).) Fuel Capacities Max Useable Fuel Capacity 5192 lb (2361 kg) (1 U. 23.207 as amended by Amendments 23-1 through 23. 29 August 2013 Page 25 of 27 NOTE 12: Airplanes modified per Beech drawing 130-4402 are eligible for increased weights in the Commuter Category as defined in Pilot’s Operating Handbook Supplement P/N 130-590031-219.S.G. FL-523.203. (359 kg) Extended Range Fuel Tanks Useable Fuel Capacity (total) 1581 lb. . prior to import back into the United States.S gal Extended Range Fuel Tanks Useable Fuel Capacity (one side) 790 lb.4) to (+208.TCDS IM. gal. gal.49.A. FL-522. FL521. NOTE 13: Company name change effective 3-16-07. Certification Basis per Model B300 except 14CFR §23.0) at 11 800 lb Straight line variation between points given Moment change due to retracting landing gear (-8 307 in.lb.3) to (+208. Airworthiness limitations changes are defined Airworthiness Limitations Manual Supplement P/N 130-590031-221. with the Wing Hardpoints installed (MOD007710).201. 14004 or ASTM Spec. Ltd. Drawing 130-9022 which installs Two Pratt & Whitney of Canada.0) at 11 800 lb Straight line variation between points given Moment change due to retracting landing gear (-8 307 in. 3 Jet Fuel and Commonwealth of Independent States (CIS) RT & TS-1 Fuels.) NOTE 17: B300 and B300C airplanes modified by Hawker Beechcraft Field Service Kit. and 23.3) to (+208. NOTE 16: B300 and B300C Airplanes modified per Hawker Beechcraft Drawing 130M000009 or Kit Drawing 130-4030 are eligible for increased weights in the commuter category as defined by Pilot’s Operating Handbook and EASA/FAA Approved Airplane Flight Manual (POH/AFM). 91/96. 29 August 2013 Page 26 of 27 Certification basis as per Model B300 except 14CFR 23. and JET B conforming to P&WC S. D1655. JET A.TCDS IM.lb. JET A-1.201. 23. Range (Landing Gear Extended) (+203. Oil P&WC PT6 Engine Service Bulletin No. JP-8 (MIL-T-83133).49.207 as amended by Amendments 23-1 through 23-50. Chinese No. or Grades 80/87. JP-5 (MIL-T-5624). 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. P/N 130-590031-245 and POH/AFM Supplement for heavy weight aircraft without ER tanks P/N 130590031-321 . 100 or 100LL aviation gasoline per ASTM D910.0) at 16 500 lb (+191.203. Contact Hawker Beechcraft Corporation as necessary to obtain availability information concerning the drawings and kits. 23.4) to (+208. . EASA Approval ref 10040288 JP-4.A.B. which are referenced by this publication. Alternate use of aviation gasoline: Use of Grades 80. PT6A-67A (turboprop) per Beech Specification BS 383843. The areas of change from a standard B300 and B300C are listed below: Design Weights Max Ramp Weight Max Takeoff Weight Max Landing Weight Max Zero Weight 16 600 lb (7 530 kg) 16 500 lb (7 484 kg) 15 675 lb (7 110 kg) 13 000 lb (5 897 kg) C. It is not necessary to purge the unused fuel from the system when switching fuel types. 14001 lists approved brand oils (Engine & Gearbox) Engine Limits Shaft Horsepo wer Torqu e% N1 gas generator speed Prop shaft speed RPM Max permissible turbine Interstage Temp Co Fuel Take Off Max Continuous Starting Transient (20 sec) 1050 1050 100% 100% 104% 104% 1700 1700 1870 850 840 870 .205. 23.G.277 Issue 05. 244 ft.0° ± 0. Diameter: 105 in. minimum starting Minus 40°C. lbs *See Note 4. Oil temperatures: Minus 40°C. It must be possible to achieve these settings without exceeding ITT or N¹ limits.A. Reverse -14° ± 0. 29 August 2013 Max Reverse (1 min) 900 1650 Page 27 of 27 760 *100% torque – 3.TCDS IM. Pitch setting at: Flight idle stop See NOTE 5. The POH provides static torque settings for takeoff. No further reduction permitted. max. . to 110°C. Under these conditions the placarded torquemeter limitations shall not be exceeded. continuous Propeller and Propeller Limits Two Hartzell HC-E4A-3M hubs with Hartzell E10478SK blades.277 Issue 05. to 110°C.5° Feathered +80. low idle 0°C. 2013 . 1996 Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26. minimum allowable for repair: 104 in. At low altitude and low ambient temperature the engines may produce more power at takeoff than that for which the airplane has been certificated. 2007 Hawker Beechcraft Corporation transferred to Beechcraft Corporation on April 12.5° Minimum idle speed 1050 rpm VI Type Certificate Holder Record: Beech Aircraft Corporation transferred to Raytheon Aircraft Company on April 15. (maximum).