TCDS H88EU

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET No. H88EU This data sheet, which is part of Type Certificate No. H88EU 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 Donauwoerth Germany I. Model EC135P1 (Normal Category) Helicopter, Approved July 31, 1996 Engines. 2 Pratt &Whitney Canada PW 206 B Fuel. See Rotorcraft Flight Manual Installed Engine Limits. Gas Generator Output Shaft Speed N-1 Torque % % (RPM) Output Shaft Speed N-2 % (RPM) Measured Gas Temperature oC ( oF) Normal Operation Takeoff power (5 min.) 75 98.7 (57250) 104 (6134) 854 (1569) Max Continuous 69 97.4 (56500) 104 (6134) 820 (1508) One Engine Inoperative 2.5 min. power 100 102.4 (59400) 104 (6134) 930 (1706) Max. Continuous 86 100.4 (58250) 104 (6134) 885 (1625) See Rotorcraft Flight Manual for other limitations including speed and temperature transients Rotor Limits. Min. Continuous Max. Continuous Power On % 95 104 Power Off % 80 for gross mass up to 1900 kg (4189 lb) 85 for gross mass above 1900 kg (4189 lb) 106 Airspeed Limits (IAS). Max. v NE = 155 kts. 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 1840 kg (4057 lb): 4180 mm (164.6 in.) aft of datum at 2720 kg (5996 lb): 4219 mm (166.1 in.) aft of datum at 2835 kg (6250 lb): 4224 mm (166.3 in.) aft of datum Max. rearward range: at 1500 kg (3307 lb): 4570 mm (179.90 in.) aft of datum at 2720 kg (5996 lb): 4387 mm (172.72 in.) aft of datum at 2835 kg (6250 lb): 4369 mm (172.0 in.) aft of datum Straight-line variation between points given. Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Rev. No. 17 17 8 8 17 8 17 14 15 17 17 14 17 17 H88EU Revision 17 AIRBUS HELICOPTERS DEUTSCHLAND GmbH EC135P1 EC135T1 EC135P2 EC135T2 EC135P2+ EC135T2+ EC635T2+ EC135P3 EC135T3 May 8, 2026 Page 2 H88EU Lateral C.G. Limits Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane. Empty Weight C.G. Range. None Max. Weight. 2720 kg (5996 lb) (Max GW 2835 kg (6250 lb) with S/B EC135-11-003 incorporated. See FMS 9.1-3) Min. Crew. One Pilot Passengers. Six (or 7 if the kit described in FMS 9.2-31 is installed and operated) Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) Max. loading: 1130 kg (2491 lb) Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank) usable: 670.5 liters (177.1 US gal.) (standard fuel tank) Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank) usable: 664 liters (175.4 US gal.) (self-sealing fuel tank) Oil Capacity. Engine oil capacity: 4.5 liter (1.19 US gal.) included in minimum gross weight Max. Operating Altitude. 6096 m (20000 ft.) Rotor blade and Control Movements. For rigging information, refer to the EC135 Maintenance Manual. II. Model EC135T1 (Normal Category) Helicopter, Approved September 17, 1996 Engines. 2 Safran Helicopter Engines ARRIUS 2B1/2B1A/2B1A1 Fuel. See Rotorcraft Flight Manual Installed Engine Limits (ARRIUS 2B1) – See NOTE 1 Output Shaft Torque % Gas Generator Speed N-1 % (RPM) Output Shaft Speed N-2 % (RPM) Measured Gas Temperature oC ( oF) Normal Operation Takeoff power (5 min.) 75 101.1 (54706) 104 (6134) 895 (1643) Max Continuous 69 98.7 (53406) 104 (6134) 855 (1571) One Engine Inoperative 2.5 min. power 100 103.7 (56113) 104 (6134) 945 (1733) Max. Continuous 86 101.1 (54706) 104 (6134) 895 (1643) See Rotorcraft Flight Manual for other limitations including speed and temperature transients Installed Engine Limits (ARRIUS 2B1A) – (After SB EC135-71-008. See FMS 9.2-57). Output Shaft Torque % Gas Generator Speed N-1 % (RPM) Output Shaft Speed N-2 % (RPM) Measured Gas Temperature oC ( oF) Normal Operation Takeoff power (5 min.) 75 101.1 (54706) 104 (6134) 895 (1643) Max Continuous 69 98.7 (53406) 104 (6134) 855 (1571) One Engine Inoperative 2.5 min. power 119.8 103.7 (56113) 104 (6134) 945 (1733) Max. Continuous 86 101.1 (54706) 104 (6134) 895 (1643) See Rotorcraft Flight Manual for other limitations including speed and temperature transients Page 3 H88EU II. Model EC135T1 (Normal Category) Helicopter, Approved September 17, 1996 – (Cont’d) Installed Engine Limits (ARRIUS 2B1A_1) – (S/N 0188 and Subsequent or After SB EC135-71-015. See FMS 9.2-62). Output Shaft Torque % Gas Generator Speed N-1 % (RPM) Output Shaft Speed N-2 % (RPM) Measured Gas Temperature oC ( oF) Normal Operation Takeoff power (5 min.) 75 101.1 (54706) 104 (6134) 895 (1643) Max Continuous 69 98.7 (53406) 104 (6134) 855 (1571) One Engine Inoperative 2.5 min. power 128 103.7 (56113) 104 (6134) 945 (1733) Max. Continuous 86 101.1 (54706) 104 (6134) 895 (1643) See Rotorcraft Flight Manual for other limitations including speed and temperature transients Rotor Limits. Power On % Power Off % Min. Continuous 95 80 for gross mass up to 1900 kg (4189 lb) 85 for gross mass above 1900 kg (4189 lb) Max. Continuous 104 106 Airspeed Limits (IAS). Max. v NE = 155 kts. 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 1840 kg (4057 lb): 4180 mm (164.6 in.) aft of datum at 2720 kg (5996 lb): 4219 mm (166.1 in.) aft of datum at 2835 kg (6250 lb): 4224 mm (166.3 in.) aft of datum Max. rearward range: at 1500 kg (3307 lb): 4570 mm (179.90 in.) aft of datum at 2720 kg (5996 lb): 4387 mm (172.72 in.) aft of datum at 2835 kg (6250 lb): 4369 mm (172.0 in.) aft of datum Straight-line variation between points given. Lateral C.G. Limits Max. deviation 100mm (3.94 in.) left or right of the fuselage median plane. Empty Weight C.G. Range None Maximum Weight. 2720 kg (5996 lb) (Max GW 2835 kg (6250 lb) with S/B EC135-11-003 R01 or higher incorporated. See FMS 9.1-3) Minimum Crew. One Pilot Passengers. Six (or 7 if the kit described in FMS 9.2-31 is installed and operated) Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) Max. loading: 1130 kg (2491 lb) Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank) Usable: 670.5 liters (177.1 US gal.) (standard fuel tank) Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank) Usable: 664 liters (175.4 US gal.) (self-sealing fuel tank) Oil Capacity. Engine oil capacity: 4.85 liters (1.28 US gal.) included in minimum gross weight Maximum Operating Altitude. 6096 m (20000 ft) Rotorblade and Control Movements. For rigging information refer to the EC135 Maintenance Manual. Page 4 H88EU III. Model EC135P2 (Normal Category) Helicopter, Approved September 6, 2001 The Model EC 135 P2 is the same as the EC 135P1 except for the installation of the Pratt & Whitney PW206B2 engine which includes new OEI power ratings. Engines. 2 Pratt & Whitney Canada PW 206 B2 Fuel. See Rotorcraft Flight Manual Installed Engine Limits. Gas Generator Output Shaft Speed N-1 Torque % % (RPM) Output Shaft Speed N-2 % (RPM) Measured Gas Temperature oC ( oF) Normal Operation Takeoff power (5 min.) 75 98.7 (57250) 104 (6165) 869 (1596) Max Continuous 69 97.4 (56500) 104 (6165) 835 (1535) One Engine Inoperative 30 sec. power 128 104.3 (60500) 104 (6165) 990 (1814) 2 min. power 125 102.6 (59500) 104 (6165) 950 (1742) Max. Continuous 86 100.4 (58250) 104 (6165) 900 (1652) See Rotorcraft Flight Manual for other limitations including speed and temperature transients Rotor Limits. Power On % Power Off % Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 85 for gross mass above 1900 kg (4189 lb) Max. Continuous 104 106 Airspeed Limits (IAS). Max. v NE = 155 kts. 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 1840 kg (4057 lb): 4180 mm (164.6 in.) aft of datum at 2835 kg (6250lb): 4224 mm (166.3 in.) aft of datum Max. rearward range: at 1500kg (3307 lb): 4570mm (179.9 in.) aft of datum at 2835kg (6250lb): 4369mm (172.0 in.) aft of datum Straight-line variation between points given. Lateral C.G. Limits Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane. Empty Weight C.G. Range. None Max. Weight. 2835 kg (6250 lb) Min. Crew. One Pilot Passengers. Six (or seven if the kit described in FMS 9.2-31 is installed and operated) Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) Max. loading: 1130 kg (2491 lb) Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank, up to S/N 249) Usable: 670.5 liters (177.1 US gal.) (standard fuel tank, up to S/N 249) Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank, up to S/N 249) Usable: 664 liters (175.4 US gal.) (self-sealing fuel tank, up to S/N 249) Total: 710 liters (187.6 US gal.) (standard fuel tank, S/N 250 and subsequent) Usable: 700.5 liters (185.1 US gal.) (standard fuel tank, S/N 250 and subsequent) Total: 701 liters (185.2 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) Page 5 H88EU Usable: 691.6 liters (182.7 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) Oil Capacity. Engine oil capacity: 4.5 liters (1.19 US gal.) included in minimum gross weight Max. Operating Altitude. 6096 m (20000 ft.) Rotor blade and Control Movements. For rigging information, refer to the EC135 Maintenance Manual. IV. Model EC135T2 (Normal Category) Helicopter, Approved November 25, 2002 The Model EC 135 T2 is the same as the EC 135 T1 except for the installation of Safran Helicopter Engines Arrius 2B2 engines, which includes new OEI power ratings. Engines. 2 Safran Helicopter Engines ARRIUS 2B2 Fuel. See Rotorcraft Flight Manual Installed Engine Limits (ARRIUS 2B2). Output Shaft Gas Generator Speed N-1 Output Shaft Speed N-2 Measured Gas Temperature Torque % Normal Operation % (RPM) % (RPM) oC (oF) Takeoff power (5 min.) 75 100 (54117) 104 (6134) 897 (1647) Max Continuous 69 99 (53576) 104 (6134) 879 (1614) One Engine Inoperative 30 second power 128 105 (56823) 104 (6134) 1024 (1875) 2.0 min. power 125 103.5 (56011) 104 (6134) 994 (1821) Max. Continuous 86 101.3 (54821) 104 (6134) 942 (1728) See Rotorcraft Flight Manual for other limitations including speed and temperature transients Rotor Limits. Power On % Power Off % Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 85 for gross mass above 1900 kg (4189 lb) Max. Continuous 104 106 Airspeed Limits (IAS). Max. v NE = 155 kts. 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 1840 kg (4057 lb): 4180 mm (164.6 in.) aft of datum at 2835 kg (6250 lb): 4224 mm (166.3 in.) aft of datum Max. rearward range: at 1500 kg (3307 lb): 4570 mm (179.9 in.) aft of datum at 2835 kg (6250 lb): 4369 mm (172.0 in.) aft of datum Straight line variation between points given. Lateral C.G. Limits Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane. Empty Weight C.G. Range None Maximum Weight. 2835 kg (6250 lb) Minimum Crew. One Pilot Passengers. Six (or seven if the kit described in FMS 9.2-31 is installed and operated) Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) Max. loading: 1130 kg (2491 lb) Page 6 H88EU IV. Model EC135T2 (Normal Category) Helicopter, Approved November 25, 2002 – (Cont’d) Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank, up to S/N 249) Usable: 670.5 liters (177.1 US gal.) (standard fuel tank, up to S/N 249) Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank, up to S/N 249) Usable: 664 liters (175.4 US gal.) (self-sealing fuel tank, up to S/N 249) Total: 710 liters (187.6 US gal.) (standard fuel tank, S/N 250 and subsequent) Usable: 700.5 liters (185.1 US gal.) (standard fuel tank, S/N 250 and subsequent) Total: 701 liters (185.2 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) Usable: 691.6 liters (182.7 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) Oil Capacity. Engine oil capacity: 4.85 liters (1.28 US gal.) included in minimum gross weight Maximum Operating Altitude. 6096 m (20000) ft. Rotor blade and Control Movements. For rigging information refer to the EC135 Maintenance Manual. V. Model EC135P2+ (Normal Category) Helicopter, Approved October 19, 2006 The Model EC135P2+ is the same as the EC135P2 except for maximum takeoff mass of 2910 kg / 2950 kg, and new power ratings AEO TOP & OEI MCP). See NOTE 5 Engines. 2 Pratt & Whitney Canada PW 206 B2 Fuel. See Rotorcraft Flight Manual Installed Engine Limits. Gas Generator Output Shaft Speed N-1 Output Shaft Speed N-2 Measured Gas Temperature Torque % % (RPM) % (RPM) oC (oF) Normal Operation Takeoff power (5 min.) 78 98.7 (57250) 104 (6165) 869 (1596) Max Continuous 69 97.4 (56500) 104 (6165) 835 (1535) One Engine Inoperative 30 sec. power 128 104.3 (60500) 104 (6165) 990 (1814) 2 min. power 125 102.6 (59500) 104 (6165) 950 (1742) Max. Continuous 89.5 100.4 (58250) 104 (6165) 900 (1652) See Rotorcraft Flight Manual for other limitations including speed and temperature transients Rotor Limits. Power On % Power Off % Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 85 for gross mass above 1900 kg (4189 lb) Max. Continuous 104 106 Airspeed Limits (IAS). Max. v NE = 155 kts. 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 1840 kg (4057 lb): 4180.0 mm (164.6 in.) aft of datum at 2910 kg (6415 lb): 4227.3 mm (166.43 in.) aft of datum at 2950 kg (6504 lb): 4229.3 mm (166.51 in.) aft of datum Max. rearward range: at 1500 kg (3307 lb): 4570.0 mm (179.9 in.) aft of datum at 2910 kg (5996 lb): 4369.0 mm (172.0 in.) aft of datum at 2950 kg (6504 lb): 4362.6 mm (171.75 in.) aft of datum Straight line variation between points given. Lateral C.G. Limits Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane. Page 7 H88EU Empty Weight C.G. Range. None Maximum Weight. 2910 kg (6415 lb) / 2950 kg (6504 lb) Note: Operation of the aircraft with MTOW up to 2950 kg is only permitted in accordance with FMS 9.1-5, FMS 9.1-6 and FMS 9.1-7 from S/N 1055 and subsequent, or after SB EC135-62-028. Minimum Crew. One Pilot Passengers. Six (or 7 if the kit described in FMS 9.2-31 is installed and operated) Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) Max. loading: 1130 kg (2491 lb) Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank, up to S/N 249) Usable: 670.5 liters (177.1 US gal.) (standard fuel tank, up to S/N 249) Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank, up to S/N 249) Usable: 664 liters (175.4 US gal.) (self-sealing fuel tank, up to S/N 249) Total: 710 liters (187.6 US gal.) (standard fuel tank, S/N 250 and subsequent) Usable: 700.5 liter (185.1 US gal.) (standard fuel tank, S/N 250 and subsequent) Total: 701 liters (185.2 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) Usable: 691.6 liters (182.7 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) Oil Capacity. Engine oil capacity: 4.5 liters (1.19 US gal.) included in minimum gross weight Max. Operating Altitude. 6096 m (20000 ft) Rotor blade and Control Movements. For rigging information, refer to the EC135 Maintenance Manual. VI. Models EC135T2+ and EC635T2+ (Normal Category) Helicopter, EC135T2+ Approved October 19, 2006 and EC635T2+ Approved October 30, 2019 Data pertinent to both models. The Models EC135T2+ and EC635T2+ are the same as the EC135T2 except for maximum takeoff mass of 2910 kg / 2950 kg, and new power ratings AEO TOP & OEI MCP). See NOTE 5 Engines. 2 Safran Helicopter Engines ARRIUS 2B2 Fuel. See Rotorcraft Flight Manual Installed Engine Limits (ARRIUS 2B2). Gas Generator Output Shaft Measured Gas Output Shaft Torque % Normal Operation Speed N-1 % (RPM) Speed N-2 % (RPM) Temperature oC ( oF) Takeoff power (5 min.) 78 100 (54117) 104 (6134) 897 (1647) Max Continuous 69 99 (53576) 104 (6134) 879 (1614) One Engine Inoperative 30 second power 128 105.0 (56823) 104 (6134) 1024 (1875) 2.0 min. power 125 103.5 (56011) 104 (6134) 994 (1821) Max. Continuous 89.5 101.3 (54821) 104 (6134) 942 (1728) See Rotorcraft Flight Manual for other limitations including speed and temperature transients Rotor Limits. Power On % Power Off % Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 85 for gross mass above 1900 kg (4189 lb) Max. Continuous 104 106 Page 8 H88EU Airspeed Limits (IAS). Max. v NE = 155 kts. 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 1840 kg (4057 lb): 4180.0 mm (164.6 in.) aft of datum at 2910 kg (6415 lb): 4227.3 mm (166.43 in.) aft of datum at 2950 kg (6504 lb): 4229.3 mm (166.51 in.) aft of datum Max. rearward range: at 1500 kg (3307 lb): 4570.0 mm (179.9 in.) aft of datum at 2910 kg (5996 lb): 4369.0 mm (172.0 in.) aft of datum at 2950 kg (6504 lb): 4362.6 mm (171.75 in.) aft of datum Straight-line variation between points given. Lateral C.G. Limits Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane. Empty Weight C.G. Range None Maximum Weight. 2910 kg (6415 lb) / 2950 kg (6504 lb) Note: Operation of the aircraft with MTOW up to 2950 kg is only permitted in accordance with FMS 9.1-5, FMS 9.1-6 and FMS 9.1-7 from S/N 1055 and subsequent, or after SB EC135-62-028. Minimum Crew. One Pilot Passengers. Six (or 7 if the kit described in FMS 9.2-31 is installed and operated) Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) Max. loading: 1130 kg (2491 lb) Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank, up to S/N 249) Usable: 670.5 liters (177.1 US gal.) (standard fuel tank, up to S/N 249) Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank, up to S/N 249) Usable: 664 liters (175.4 US gal.) (self-sealing fuel tank, up to S/N 249) Total: 710 liters (187.6 US gal.) (standard fuel tank, S/N 250 and subsequent) Usable: 700.5 liter (185.1 US gal.) (standard fuel tank, S/N 250 and subsequent) Total: 701 liters (185.2 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) Usable: 691.6 liters (182.7 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) Oil Capacity. Engine oil capacity: 4.85 liters (1.28 US gal.) included in minimum gross weight Maximum Operating Altitude. 6096 m (20000 ft.) Rotor blade and Control Movements. For rigging information, refer to the EC135 Maintenance Manual. Additional Information. SN 0858 was converted from an EC635T2+ to an EC135T2+ with the application of major modification E6065 via Airbus Helicopters SB-EC135-00-002. The aircraft has two data plates identifying it as a converted EC635T2+ and carries the same certification basis and same continued airworthiness requirements as an EC135T2+. See NOTE 7. VII. Model EC135P3 (Normal Category) Helicopter, Approved September 3, 2015, Revised March 6, 2023 For Models EC135P3 equipped with avionics configuration HELIONIX (Mod E-2698), see Note 5. Engines. 2 Pratt & Whitney Canada PW 206 B3 Fuel. See Rotorcraft Flight Manual Installed Engine Limits. Gas Generator Output Shaft Speed N-1 Output Shaft Speed N-2 Measured Gas Temperature (TOT) Page 9 H88EU Torque % % % oC ( oF) Normal Operation Takeoff power (5 min.) 78 99.8 105.5 900 (1652) Max Continuous 69 97.4 105.5 835 (1535) One Engine Inoperative 30 sec. power 128 104.3 104.5 990 (1814) 2 min. power 125 102.6 104.5 950 (1742) Max. Continuous 89.5 99.8 104.5 900 (1652) See Rotorcraft Flight Manual for other limitations including speed and temperature transients Rotor Limits. Power On % Power Off % Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 85 for gross mass above 1900 kg (4189 lb) Max. Continuous 105.5 106 Airspeed Limits (IAS). Max. v NE = 150 kts. 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 2039 kg (4495 lb): 4152 mm (163.5 in.) aft of datum at 2980 kg (6569 lb): 4201 mm (165.4 in.) aft of datum Max. rearward range: at 1600 kg (3527 lb): 4555 mm (179.3 in.) aft of datum at 2980 kg (6569 lb): 4369 mm (172 in.) aft of datum For Models EC135P3 equipped with avionics configuration HELIONIX (Mod E-2698) Max. forward range: at 2150 kg (4740 lb): 4121 mm (162.2 in.) aft of datum at 2980 kg (6569 lb): 4171 mm (164.2 in.) aft of datum at 3100 kg (6834 lb): 4178 mm (164.5 in.) aft of datum Max. rearward range: at 1700 kg (3748 lb): 4541 mm (178.8 in.) aft of datum at 2980 kg (6569 lb): 4369 mm (172 in.) aft of datum at 3100 kg (6834 lb): 4353 mm (171.4 in.) aft of datum Straight-line variation between points given. Lateral C.G. Limits Max. deviation: 100 mm (3.94 in.) left or right of the fuselage median plane. For Models EC135P3 equipped with avionics configuration HELIONIX (Mod E-2698) Max. deviation 50 mm (1.97 in.) left or right of the fuselage median plane. Empty Weight C.G. Range. None Maximum Weight. 2980 kg (6569 lb) Flight with increased gross weight above 2980 kg (6569 lb) up to 3100 kg (6834 lb) is permitted only in accordance with FMA 11-11. Minimum Crew. One Pilot Passengers. Seven Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) Max. loading: 1130 kg (2491 lb) Fuel Capacity. Total: 680 liters (179.6 US gal.) Usable: 670.5 liters (177.1 US gal.) Total: 710 liters (187.6 US gal.) Usable: 700.5 liters (185.1 US gal.) Oil Capacity. Engine oil capacity: 4.5 liters (1.19 US gal.) included in minimum gross weight Max. Operating Altitude. 6096 m (20000 ft.) Page 10 H88EU Rotor blade and Control Movements. For rigging information, refer to the EC135 Maintenance Manual. VIII. Model EC135T3 (Normal Category) Helicopter, Approved September 3, 2015, Revised March 6, 2023 For Models EC135T3 equipped with avionics configuration HELIONIX (Mod E-2698), see Note 5. Engines. 2 Safran Helicopter Engines ARRIUS 2B2 Fuel. See Rotorcraft Flight Manual Installed Engine Limits (ARRIUS 2B2). Output Shaft Gas Generator Speed N-1 Output Shaft Speed N-2 Measured Gas Temperature (TOT) Torque % Normal Operation % % oC (oF) Takeoff power (5 min.) 78 86.1-100 106 897 (1647) Max Continuous 69 85.3-99 106 879 (1614) One Engine Inoperative 30 second power 128 91.7-104.8 106 1024 (1875) 2.0 min. power 125 91.7-103.5 106 994 (1821) Max. Continuous 89.5 87.4-101.25 106 942 (1728) See Rotorcraft Flight Manual for other limitations including speed and temperature transients Rotor Limits. Power On % Power Off % Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 85 for gross mass above 1900 kg (4189 lb) Max. Continuous 105.5 106 Airspeed Limits (IAS). Max. v NE = 150 kts. 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 2039 kg (4495 lb): 4152 mm (163.5 in.) aft of datum at 2980 kg (6569 lb): 4201 mm (165.4 in.) aft of datum Max. rearward range: at 1600 kg (3527 lb): 4555 mm (179.3 in.) aft of datum at 2980 kg (6569 lb): 4369 mm (172 in.) aft of datum For Models EC135T3 equipped with avionics configuration HELIONIX (Mod E-2698) Max. forward range: at 2150 kg (4740 lb): 4121 mm (162.2 in.) aft of datum at 2980 kg (6569 lb): 4171 mm (164.2 in.) aft of datum