TCDS H13EU

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET No. H13EU This data sheet, which is part of Type Certificate No. H13EU 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: AIRBUS HELICOPTERS DEUTSCHLAND GmbH (AHD) D-86609 Donauwörth Germany Type Certificate Holder Record: Eurocopter Deutschland GmbH changed name to Airbus Helicopters Deutschland GmbH on January 7, 2014. I. Model MBB-BK 117 A-1 (Transport Category A&B) Helicopter, Approved March 29, 1983. Engines. 2 Lycoming LTS 101-650 B-1 Fuel. See Rotorcraft Flight Manual. Installed Engine Limits Normal Operation Output Shaft Torque % (Ft-Lbs.) Gas Generator Speed N-1 % (RPM) Output Shaft Speed N-2 % (RPM) Measured Gas Temperature °C (°F) Takeoff power (5 min.) 71 (368) 102.7 (49159) 102 (6120) 782 (1440) Max. continuous 71 (368) 102.7 (49159) 102 (6120) 763 (1405) One Engine Inoperative 2.5 minutes power 100 (519) 105.6 (50548) 102 (6120) 832 (1528) 30 minutes power 91.5 (475) 104.8 (50469) 102 (6120) 796 (1463) Max. continuous 83 (431) 102.7 (49159) 102 (6120) 763 (1404) See Rotorcraft Flight Manual for other limitations including speed and temperature transients. Rotor Limits. Min. Continuous Power On, % (RPM) Power Off, %(RPM) gross weight up to 4409 lbs. 98 (376) 80 (307) gross weight 4409 - 6283 lbs. 98 (376) 85 (326) Max. Continuous 102 (391) 104 (399) Max. Transient 106 (406) 110 (422) Min. Transient 85 (326) --- Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 26 6 13 13 13 6 13 13 19 26 26 26 26 17 24 20 25 18 25 25 H13EU Revision 26 AIRBUS HELICOPTERS DEUTSCHLAND GmbH MBB-BK 117 A-1 MBB-BK 117 A-3 MBB-BK 117 A-4 MBB-BK 117 B-1 MBB-BK 117 B-2 MBB-BK 117 C-1 MBB-BK 117 C-2 MBB-BK 117 D-2 MBB-BK 117 D-3 March 5, 2026 2 H13EU I. Model MBB-BK 117 A-1 (Transport Category A&B) Helicopter, Approved March 29, 1983. (cont'd) Airspeed Limits (IAS). Max. V NE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with outside air temperature and altitude. C.G. Range. Longitudinal C.G. Limits Max. forward range: up to 3747.8 lb: 172.2 in. aft of datum up to 4409.2 lb: 170.7 in. aft of datum up to 6283.1 lb: 173.8 in. aft of datum Max. rearward range: up to 3747.8 lb: 183.9 in. aft of datum up to 6283.1 lb: 179.7 in. aft of datum Straight line variation between points given. Lateral C.G. Limits. Max. deviation 3.9 in right or left of the fuselage median plane. Empty Weight C.G. Range. None Max. Weight. 6283 lbs. Min. Crew. 1 (right-hand seat only). Passengers. 7 (See NOTE 1A). Max. Baggage. Max. permissible floor loading: 123 lb/sq. ft. Max. loading: 2645 lb Aft of rear seat bank: 551 lb Fuel Capacity. 160.5 US gal. (1071.6 lb., 179.6 in.) total; 158.0 US gal. (1054.9 lb.) usable: 132.5 US gal. (884.5 lb., 179.88 in.) in main tank, and 25.5 US gal. (170.4 lb., 187.36 in.) in supply tank. (See NOTE 1B) Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight 2 x 1.14 US gal. (176.77 in.). Main transmission oil has been included with the minimum gross weight 3.3 US gal. (176.38 in.) Max. Operating Altitude. See Rotorcraft Flight Manual, Model MBB-BK 117 A-1. Rotor Blade and Control For rigging information refer to the MBB Model MBB-BK 117 Maintenance Manual. Movements 3 H13EU II. Model MBB-BK 117 A-3 (Transport Category A&B) Helicopter, Approved September 10, 1985. Engines. 2 Lycoming LTS 101-650B-1 Fuel. See Rotorcraft Flight Manual. Installed Engine Limits Normal Operation Output Shaft Torque % (Ft-Lbs.) Gas Generator Speed N-1 % (RPM) Output Shaft Speed N-2 % (RPM) Measured Gas Temperature °C (°F) Takeoff power (5 min.) 71 (368) 102.7 (49159) 102 (6120) 782 (1440) Max. continuous 71 (368) 102.7 (49159) 102 (6120) 763 (1405) One Engine Inoperative 2.5 minutes power 100 (519) 105.6 (50548) 102 (6120) 832 (1528) 30 minutes power 91.5 (475) 104.8 (50469) 102 (6120) 796 (1463) Max. continuous (See Note 6.) 83 (431) 102.7 (49159) 102 (6120) 763 (1404) See Rotorcraft Flight Manual for other limitations including speed and temperature transients. Rotor Limits. Min. Continuous Power On, % (RPM) Power Off, %(RPM) gross weight up to 4409 lbs. 98 (376) 80 (307) gross weight 4409 - 6283 lbs. 98 (376) 85 (326) Max. Continuous 102 (391) 104 (399) Max. Transient 106 (406) 110 (422) Min. Transient 85 (326) --- Airspeed Limits (IAS). Max. V NE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with outside air temperature and altitude. C.G. Range. Longitudinal C.G. Limits Max. forward range: at 3748 lb: 172.2 in. aft of datum at 4409 lb: 170.7 in. aft of datum at 7055 lb: 175.1 in. aft of datum Max. rearward range: at 3748 lb: 183.9 in. aft of datum at 7055 lb: 178.5 in. aft of datum Straight-line variation between points given. Lateral C.G. Limits. Up to 6283 lb.: Max. deviation 3.94 in. right or left of the fuselage median plane. Above 6283 lb.: Max. deviation 3.15 in. right or left of the fuselage median plane. Empty Weight C.G. Range. None. Max. Weight. 7055 lb. Min. Crew. 1 (right-hand seat only). Passengers. 7 (See NOTE 1A). Max. Baggage. Max. permissible floor loading: 123 lb/sq. ft. Max. loading: 2645 lb. Aft of rear seat bank: 551 lb. 4 H13EU II. Model MBB-BK 117 A-3 (Transport Category A&B) Helicopter, Approved September 10, 1985. (cont'd) Fuel Capacity. 160.5 US gal. (1071.6 lb., 179.6 in.) total; 158.0 US gal. (1054.9 lb.) usable: 132.5 US gal. (884.5 lb., 179.88 in.) in main tank, and 25.5 US gal (170.4 lb., 187.36 in.) in supply tank. (See NOTE 1B) Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight 2 x 1.4 US gal. (176.77 in.). Main transmission oil has been included with the minimum gross weight 3.3 US gal. (176.77 in.). Max. Operating Altitude. See Rotorcraft Flight Manual, MBB BK-117 A-3. Rotor Blade and Control For rigging information refer to the MBB Model BK 117 Maintenance Manual. Movement III. Model MBB-BK 117 A-4 (Transport Category A&B) Helicopter, Approved April 24, 1987. Engine. 2 Lycoming LTS 101-650B-1 Fuel. See Rotorcraft Flight Manual. Installed Engine Limits Normal Operation Output Shaft Torque % (Ft-Lbs.) Gas Generator Speed N-1 % (RPM) Output Shaft Speed N-2 % (RPM) Measured Gas Temperature °C (°F) Takeoff power 83 (430) 102.7 (49159) 102 (6120) 782 (1440) Max. continuous 71 (368) 102.7 (49159) 102 (6120) 763 (1405) One Engine Inoperative 2.5 minutes power 100 (519) 105.6 (50548) 102 (6120) 832 (1528) 30 minutes power 91.5 (475) 104.8 (50469) 102 (6120) 796 (1463) Max. continuous (See Note 6.) 83 (431) 102.7 (49159) 102 (6120) 763 (1404) See Rotorcraft Flight Manual for other limitations including speed and temperature transients. Rotor Limits. Min. Continuous Power On, % (RPM) Power Off, %(RPM) gross weight up to 4409 lbs. 98 (376) 80 (307) gross weight 4409 - 6283 lbs. 98 (376) 85 (326) Max. Continuous 102 (391) 104 (399) Max. Transient 106 (406) 110 (422) Min. Transient 85 (326) --- Airspeed Limits (IAS). Max. V NE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with outside air temperature and altitude. C.G. Range. Longitudinal C.G. Limits (Straight-line variation between points given.) Max. forward range: at 3748 lb: 172.2 in. aft of datum at 4409 lb: 170.7 in. aft of datum at 7055 lb: 175.1 in. aft of datum Max. rearward range: at 3748 lb: 183.9 in. aft of datum at 7055 lb: 178.5 in. aft of datum 5 H13EU III. Model MBB-BK 117 A-4 (Transport Category A&B) Helicopter, Approved April 24, 1987. (cont'd) Lateral C.G. Limits. Up to 6283 lb.: Max. deviation 3.84 in. right or left of the fuselage median plane. Above 6283 lb.: Max. deviation 3.15 in. right or left of the fuselage median plane. Empty Weight C.G. Range. None. Max. Weight. 7055 lb. Min. Crew. 1 (right-hand seat only). Passengers. 7 (See NOTE 1A). Max. Baggage. Max. permissible floor loading: 123 lb/sq. ft. Max. loading: 2645 lb. Aft of rear seat bank: 551 lb. Fuel Capacity. 160.5 US gal. (1071.6 lb., 179.6 in.) total: 158.0 US gal (1054.8 lb.) usable: 132.5 US gal. (884.5 lb., 179.6 in.) in main tank, and 25.5 US gal (170.4 lb., 187.36 in.) in supply tank. (See NOTE 1B) Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight. 2 x 1.14 US gal. (176.77 in.). Main transmission oil has been included with the minimum gross weight. 3.3 US gal. (176.77 in.). Max. Operating Altitude. See Rotorcraft Flight Manual, MBB BK-117 A-4. Rotor Blade and Control For rigging information refer to the MBB Model BK 117 Maintenance Manual. Movement IV. Model MBB-BK 117 B-1 (Transport Category A & B) Helicopter, Approved December 11, 1987. Engines. 2 Lycoming LTS 101-750B-1 Fuel. See Rotorcraft Flight Manual. Installed Engine Limits Normal Operation Output Shaft Torque % (Ft-Lbs.) Gas Generator Speed N-1 % (RPM) Output Shaft Speed N-2 % (RPM) Measured Gas Temperature °C (°F) Takeoff power (5 min.) 83 (430) 102.7 (49159) 102 (6120) 786 (1447) Max. continuous 71 (368) 102.7 (49159) 102 (6120) 765 (1408) One Engine Inoperative 2.5 minutes power 100 (519) 105.6 (50548) 102 (6120) 836 (1536) 30 minutes power 91.5 (475) 104.8 (50469) 102 (6120) 800 (1471) Max. continuous (See Note 6.) 83 (431) 102.7 (49159) 102 (6120) 765 (1408) See Rotorcraft Flight Manual for other limitations including speed and temperature transients. 6 H13EU IV. Model MBB-BK 117 B-1 (Transport Category A & B) Helicopter, Approved December 11, 1987. (cont'd) Rotor Limits. Min. Continuous Power On, % (RPM) Power Off, %(RPM) gross weight up to 4409 lbs. 98 (376) 80 (307) gross weight 4409 - 6283 lbs. 98 (376) 85 (326) Max. Continuous 102 (391) 104 (399) Max. Transient 106 (406) 110 (422) Min. Transient 85 (326) --- Airspeed Limits (IAS). Max. V NE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with outside air temperature and altitude. C.G. Range. Longitudinal C.G. Limits Max. forward range: at 3748 lb: 172.2 in. aft of datum at 4409 lb: 170.7 in. aft of datum at 7055 lb: 175.1 in. aft of datum Max. rearward range: at 3748 lb: 183.9 in. aft of datum at 7055 lb: 178.5 in. aft of datum Straight line variation between points given. Lateral C.G. Limits. Up to 6283 lb.: Max. deviation 3.84 in. right or left of the fuselage median plane. Above 6283 lb.: Max. deviation 3.15 in. right or left of the fuselage median plane. Empty Weight C.G. Range. None. Max. Weight. 7055 lb. Min. Crew. 1 (right-hand seat only) Passengers. 7 (See NOTE 1A) Max. Baggage. Max. permissible floor loading 123 lb/sq. ft. Max. loading: 2645 lb. Aft of rear seat bank: 551 lb. Fuel Capacity. 160.5 US gal. (1071.6 lb., 179.6 in.) total: 158.0 US gal (1054.8 lb.) usable: 132.5 US gal. (884.5 lb., 179.6 in.) in main tank, and 25.5 US gal (170.4 lb., 187.36 in.) in supply tank. (See NOTE 1B) Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight. 2 x 1.14 US gal. (176.77 in.). Main transmission oil has been included with the minimum gross weight. 3.3 US gal. (176.77 in.) Max. Operating Altitude. See Rotorcraft Flight Manual, MBB BK-117 B-1. Rotor Blade and Control For rigging information refer to the MBB BK 117 Maintenance Manual. Movement 7 H13EU V. Model MBB-BK 117 B-2 (Transport Category A & B) Helicopter, Approved December 7, 1992. Engines. 2 Lycoming LTS 101-750B-1 Fuel. See Rotorcraft Flight Manual. Installed Engine Limits Normal Operation Output Shaft Torque % (Ft-Lbs.) Gas Generator Speed N-1 % (RPM) Output Shaft Speed N-2 % (RPM) Measured Gas Temperature °C (°F) Takeoff power (5 min.) 83 (430) 102.7 (49159) 102 (6120) 786 (1447) Max. continuous 71 (368) 102.7 (49159) 102 (6120) 765 (1408) One Engine Inoperative 2.5 minutes power 100 (519) 105.6 (50548) 102 (6120) 836 (1536) 30 minutes power 91.5 (475) 104.8 (50469) 102 (6120) 800 (1471) Max. continuous (See Note 6.) 83 (431) 102.7 (49159) 102 (6120) 765 (1408) See Rotorcraft Flight Manual for other limitations including speed and temperature transients. Rotor Limits. Min. Continuous Power On, % (RPM) Power Off, %(RPM) gross weight up to 4409 lbs. 98 (376) 80 (307) gross weight 4409 - 7385 lbs. 98 (376) 85 (326) Max. Continuous 102 (391) 104 (399) Max. Transient (max 12 sec.) 106 (406) 110 (422) Min. Transient 85 (326) --- Airspeed Limits (IAS). Max. V NE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with outside air temperature and altitude. C.G. Range. Longitudinal C.G. Limits Max. forward range: at 3748 lb: 172.2 in. aft of datum at 4409 lb: 170.7 in. aft of datum at 7385 lb: 173.2 in. aft of datum Max. rearward range: at 3748 lb: 183.9 in. aft of datum at 7385 lb: 178.0 in. aft of datum Straight line variation between points given. Lateral C.G. Limits. Up to 6283 lb.: Max. deviation 3.94 in. right or left of the fuselage median plane. Above 6283 lb.: Max. deviation 3.15 in. right or left of the fuselage median plane. Empty Weight C.G. Range. None. Max. Weight. 7385 lb. Min. Crew. 1 (right-hand seat only) Passengers. 7 (See NOTE 1A) Max. Baggage. Max. permissible floor loading 123 lb/sq. ft. Max. loading: 2645 lb. Aft of rear seat bank: 551 lb. 8 H13EU V. Model MBB-BK 117 B-2 (Transport Category A & B) Helicopter, Approved December 7, 1992. (cont'd) Fuel Capacity. 160.5 US gal. (1071.6 lb., 179.6 in.) total: 158.0 US gal (1054.8 lb) usable: 132.5 US gal. (884.5 lb., 179.6 in.) in main tank, and 25.5 US gal (170.4 lb., 187.36 in.) in supply tank. (See NOTE 1B) Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight. 2 x 1.14 US gal. (176.77 in.). Main transmission oil has been included with the minimum gross weight. 3.3 US gal. (176.77 in.) Max. Operating Altitude. See Rotorcraft Flight Manual, BK-117 B-2. Rotor Blade and Control For rigging information refer to the MBB BK 117 Maintenance Manual. Movements. VI. Model MBB-BK 117 C-1 (Transport Category A&B) Helicopter, Approved December 7, 1992. Engines 2 Turbomeca Arriel 1E2 Fuel See Rotorcraft Flight Manual. Installed Engine Limits Normal Operation Torque Limits % Gas Generator Speed N-1 % (RPM) °C Temperature TOT °C Power RPM % Takeoff power (5 min.) 83 100.6 (52111) 845 102* Max. continuous 71 100.0 (51800) 845 102* One Engine Inoperative 2.5 minutes power 125 103.3 (53509) 885 102 Max. continuous 91.5 100.3 (51955) 845 102 *Max PA > 8000 ft and V < 55 KIAS 104%. Rotor Limits. Power On, % (RPM) Power Off, %(RPM) Min. continuous 98 80 (<2000 kg) Max. continuous 102 85 (>2000 kg) 104 PA > 8000 ft + V <55 KIAS For all serial numbers See Rotorcraft Flight Manual for other limitations including speed and temperature transients. Airspeed Limits (IAS). Max. V NE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with outside air temperature and altitude. C.G. Range. Longitudinal C.G. Limits Max. forward range: at 3748 lb: 172.2 in. aft of datum at 4409 lb: 170.7 in. aft of datum at 7385 lb: 173.2 in. aft of datum Max. rearward range: at 3748 lb: 183.9 in. aft of datum at 7385 lb: 178.0 in. aft of datum 9 H13EU VI. Model MBB-BK 117 C-1 (Transport Category A&B) Helicopter, Approved December 7, 1992. (cont'd) Straight line variation between points given. Lateral C.G. Limits. Up to 6283 lb.: Max. deviation 3.94 in. right or left of the fuselage median plane. Above 6283 lb.: Max. deviation 3.15 in. right or left of the fuselage median plane. Empty Weight C.G. Range. None. Max. Weight. 7385 lb. Min. Crew. 1 (right-hand seat only) Passengers. 7 (See NOTE 1A) Max. Baggage. Max. permissible floor loading 123 lb/sq. ft. Max. loading: 2645 lb. Aft of rear seat bank: 551 lb. Fuel Capacity. 187 US gal. (1248 lb., 173.6 in.) total: 184.2 US gal (1230.2 lb.) usable: 132.5 US gal. (884.5 lb., 179.6 in.) in main tank, and 26.2 US gal 175.3 lb., 134.6 in.) in auxiliary fuel tank, and 25.5 US gal (170.4 lb., 187.36 in.) in supply tank. Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight. 2 x 1.14 US gal. (176.77 in.) Main transmission oil has been included with the minimum gross weight. 3.3 US gal. (176.77 in.). Max. Operating Altitude. See Rotorcraft Flight Manual, MBB-BK 117 C-1. Rotor Blade and Control For rigging information refer to the MBB BK 117 C Maintenance Manual. Movements. VII. Model MBB-BK 117 C-2 (Transport Category A&B) Helicopter, Approved January 17, 2002. For Serial Numbers 9004 through 19999 Engines. 2 Turbomeca ARRIEL 1E2 engines Fuel. See Rotorcraft Flight Manual. Installed Engine Limits Normal Operation Torque Limits % Gas Generator Speed N-1 % (RPM) Temperature TOT °C Power RPM % Takeoff power (5 min.) 88 101.9 (52835) 845 102* Max. continuous 71 100.0 (51995) 845 102* One Engine Inoperative 2.5 minute power 125 103.3 (53509) 885 102 Max. continuous 91.5 101.9 (52835) 845 102 *Max PA > 8000 ft and V < 55 KIAS 104%. 10 H13EU VII. Model MBB-BK 117 C-2 (Transport Category A&B) Helicopter, Approved January 17, 2002. (cont'd) Rotor Limits. Power On, % (RPM) Power Off, %(RPM) Min. continuous 96 80 (<2000 kg) Max. continuous 104 85 (>2000 kg) 104 For all serial numbers See Rotorcraft Flight Manual for other limitations including speed and temperature transients. Airspeed Limits (IAS). Max. V NE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with outside air temperature and altitude. C.G. Range. Longitudinal C.G. Limits (Straight line variation between points given.) Max. forward range: at 7900 lb: 172.2 in. aft of datum at 4409 lb: 170.7 in. aft of datum Max. rearward range: at 3858 lb: 183.7 in. aft of datum at 7900 lb: 179.0 in. aft of datum Lateral C.G. Limits. Up to 6614 lbs (3000 kg): Max. deviation 3.94 in. (100 mm) right or left of the fuselage median plane. Above 6614 lbs (3000 kg): Max. deviation 3.15 in. (80 mm) right or left of the fuselage median plane. Empty Weight C.G. Range. None. Max. Weight. 3585 (kg) (7900 lbs) Min. Crew. 1 (right-hand seat only) Passengers. standard: 9, when equipped and operated in accordance with FMS 9.2-27: ten Max. Baggage. Max. permissible floor loading 123 lb/sq. ft. Fuel Capacity. with standard fuel tank total fuel: 879.1 l usable fuel: 867.5 l with self-sealing fuel tank total fuel: 861.6 l useable fuel: 850.0 l Oil Capacity. Refer to Rotorcraft Flight Manual Max. Operating Altitude. 18000 ft. Rotor Blade and Control For rigging information refer to the MBB BK 117 C-2 Maintenance Manual. Movements. Production Basis: Production Certificate No. 343CE. The manufacturer Airbus Helicopters Inc., located in Columbus, Mississippi, is licensed by Airbus Helicopters Deutschland GmbH to manufacture the MBB-BK117 C-2 and C-2(e). S/N 9004 through 19999 may be produced by Airbus Helicopters Inc. in Columbus, Mississippi, Airbus Helicopters in France, or Airbus Helicopters Deutschland GmbH in Germany. The manufacturer can be confirmed by the aircraft data plate. Information Pertinent to the MBB-BK117 C-2(e) Effective from Serial Number 9601 if Garmin G500H cockpit is installed. Type design changes to the MBB-BK117 C-2 that install Garmin 500H avionics equipment and limit operations to VFR only have been approved. These type design changes result in a helicopter that AHD has named MBB-BK117 C-2e. EASA issued an amended type certificate (EASA.R.010 dated April 17, 2015) that identifies the MBB-BK117 C-2e. In accordance with FAR 21.19, the FAA determined that the type design changes involved did not rise to the level that required an FAA amended type certificate. However, the FAA does wish to recognize that helicopters with these type design changes exist; therefore, the designation MBB-BK117 C-2(e) will be used. See Note 12 for more information on the type design changes for MBB-BK117 C- 2(e). 11 H13EU VIII. Model MBB-BK 117 D-2 (Transport Category A&B) Helicopter, Approved October 9, 2014. Production Basis. Production Certificate No. 005 (JCAB approved Production Organization). The manufacturer Kawasaki Heavy Industries, Ltd., located in Gifu Prefecture, Japan, is licensed by Airbus Helicopters Deutschland GmbH to manufacture the MBB-BK117 D-2, S/N 20293 only. For Serial Numbers 20003 through 20999 Engines. 2 Turbomeca ARRIEL 2E engines Fuel. See Rotorcraft Flight Manual. Installed Engine Limits* Normal Operation Torque Limits % Gas Generator Speed N-1 % Temperature TOT °C Power RPM % Takeoff power (5 min.) 95 100.6 933 108.3 Max. continuous 74 98.5 916 108.3 Extended Power (30 min.) 95 100.6 933 108.3 One Engine Inoperative 30 seconds power 150 105.7 1021 108.3 2 minutes power 130 104.3 1002 108.3 Max. continuous 100 101.7 960 108.3 * See Rotorcraft Flight Manual for AEO transient limits Rotor Limits. Power On, % (RPM) Power Off, %(RPM) Min. continuous 94 80 (<2200 kg) Max. continuous 108.3 85 (>2200 kg) 109 For all serial numbers See Rotorcraft Flight Manual for other limitations including speed and temperature transients. Airspeed Limits (IAS). Max. VNE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with outside air temperature and altitude. C.G. Range. Longitudinal C.G. Limits (Straight line variation between points given.) Max. forward range: at 5289 lbs (2400 kg): 171.3 in. (4347 mm) aft of datum at 8157 lbs (3700 kg): 172.5 in. (4379 mm) aft of datum at 8377 lbs (3800 kg): 172.6 in (4383 mm) aft of datum Max. rearward range: at 4407 lbs (2000 kg): 185.2 in. (4700 mm) aft of datum at 8157 lbs (3700 kg): 178.9 in. (4540 mm) aft of datum at 8377 lbs (3800 kg): 178.1 in (4525 mm) aft of datum Lateral C.G. Limits. Up to 6614 lbs (3000 kg): Max. deviation 3.94 in. (100 mm) right or left of the fuselage median plane. Above 6614 lbs (3000 kg): Max. deviation 3.15 in. (80 mm) right or left of the fuselage median plane. Empty Weight C.G. Range. None. Max. Weight. 8157 lbs (3700kg) Alternate max weight: 8377 lbs (3800 kg) only in accordance with FMA 11-19 Min. Crew. 1 (right-hand seat only) Passengers. 9 (standard configuration) Max. Baggage. Max. permissible floor loading 123 lb/sq. ft. 12 H13EU VIII. Model MBB-BK 117 D-2 (Transport Category A&B) Helicopter, Approved October 9, 2014. (cont'd) Fuel Capacity. with standard fuel tank total fuel : 915.8 liter usable fuel : 903.8 liter Oil Capacity. Refer to Rotorcraft Flight Manual Max. Operating Altitude. 20000 ft. 16000 ft (PA/DA whichever is less) for hover in ground effect, takeoff and landing Rotor Blade and Control For rigging information refer to the MBB BK 117 D-2 Maintenance Manual. Movements. IX. Model MBB-BK 117 D-3 (Transport Category A&B) Helicopter, Approved November 25, 2020. For Serial Numbers 21001 and subsequent Production Basis: Production Certificate No. 005 (JCAB approved Production Organization). The manufacturer Kawasaki Heavy Industries, Ltd., located in Gifu Prefecture, Japan, is licensed by Airbus Helicopters Deutschland GmbH to manufacture the MBB-BK117 D-3. Production Certificate No. 343CE. The manufacturer Airbus Helicopters Inc., located in Columbus, Mississippi, is licensed by Airbus Helicopters Deutschland GmbH to manufacture the MBB-BK117 D-3. S/N 21001 and subsequent may be produced by Kawasaki Heavy Industries, Ltd. in Japan, Airbus Helicopters Inc. in Columbus, Mississippi, Airbus Helicopters in France, or Airbus Helicopters Deutschland GmbH in Germany. The manufacturer can be confirmed by the aircraft data plate. Engines. 2 Safran Helicopter Engines (former Turbomeca) ARRIEL 2E engines Fuel. See Rotorcraft Flight Manual. Installed Engine Limits* Normal Operation Torque Limits % Gas Generator Speed N-1 % Temperature TOT °C Power RPM % Max. continuous 74 98.5 916 108.3 Extended Power (30 min.) 95 100.6 933 108.3 One Engine Inoperative 30 seconds power 150 105.7 1021 108.3 2 minutes power 143 104.3 1002 108.3