TCDS H7EU

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. H7EU This data sheet, which is part of Type Certificate No. H7EU, 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: Leonardo S.p.A. Helicopter Division Piazza Monte Grappa, 4 00195 – Rome, Italy Type Certificate Holder Record: Agusta S.p.A. was previous name of TC holder. The company name change history is presented below. Type Certificate Holder Period Costruzioni Aeronautiche Giovanni Agusta Via Giovanni Agusta, 520; 21017 Cascina Costa di Samarate (VA) – Italy 28 May 1975 – 29 November 1988 Agusta S.p.A. Via Giovanni Agusta, 520; 21017 Cascina Costa di Samarate (VA) – Italy 30 November 1988 ‐ 19 December 1996 Agusta un’azienda di Finmeccanica S.p.A. Via Giovanni Agusta, 520; 21017 Cascina Costa di Samarate (VA) – Italy 20 December 1996 ‐ 27 December 1999 Agusta S.p.A. Via Giovanni Agusta, 520; 21017 Cascina Costa di Samarate (VA) – Italy 28 December 1999 ‐ 31 May 2011 AgustaWestland S.p.A. Via Giovanni Agusta, 520; 21017 Cascina Costa di Samarate (VA) – Italy 1 June 2011 ‐ 30 July 2014 AgustaWestland S.p.A. Piazza Monte Grappa, 4; 00195 Roma ‐ Italy 31 July 2014 ‐ 31 December 2015 Finmeccanica S.p.A., Helicopter Division Piazza Monte Grappa, 4; 00195 Roma ‐ Italy 1 January 2016 ‐ 14 July 2016 Leonardo S.p.A., Helicopters Piazza Monte Grappa, 4; 00195 Roma ‐ Italy since 15 July 2016 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 32 10 11 11 10 10 11 11 11 11 11 18 18 17 19 19 17 23 18 23 Page No. 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 Rev. No. 28 28 28 28 28 23 24 24 24 24 24 24 26 28 31 28 28 28 29 30 Page No. 41 42 43 44 45 46 47 Rev. No. 28 31 25 25 25 32 31 H7EU Revision 32 Leonardo Model A109 Model A109A Model A109A II Model A109C Model A109K2 Model A109E Model A119 Model A109S Model AW119 MKII Model AW109SP July 6, 2026 Page 2 of 47 H7EU, Rev 32 I. Model A109 (Normal Category Helicopter) approved June 1, 1975. Engines. Two (2) Detroit Diesel Allison Division of General Motors Corporation Model 250-C20 turboshaft engines. Bendix gas producer fuel control DP-N1. Bendix power turbine governor AL-AA1. Fuel. For all temperatures: MIL-T-5624 grade JP-4 ASTM D-1655 Jet B For temperature above -18ºC (0ºF): MIL-T-5624 grade JP-5 ASTM D-1655 Jet A ASTM D-1655 Jet A1 See Note 4 Engine Limits. All-engine operation Takeoff (5 minutes) Torque 113% (302 lb.ft) (346 shp) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 102 % (52000 rpm) Gas temperature 793ºC (1460ºF) Maximum Continuous Torque 113% (302 lb.ft)(346 shp) Output shaft speed (N2) 95-100% (5716-6016) Gas producer speed (N1) 101% (51490 rpm) Gas temperature 737ºC (1358ºF) Single-engine operation (emergency) Takeoff (5 minutes) Torque 131% (350 lb.ft)(400 shp) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 102% (52000 rpm) Gas temperature 793ºC (1460ºF) Maximum Continuous Torque 126% (336 lb.ft)(385 shp) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 101% (51490 rpm) Gas temperature 777ºC (1430ºF) (See FAA-approved Helicopter Flight Manual for rpm and temperature transient limits). Rotor Limits. Power Off Maximum Minimum Power On Maximum Minimum 110 % (424 rpm) 90 % (346 rpm) 100 % (385 rpm) 95 % (365 rpm) Rotor Speed Warning. Low Speed High Speed 95 % (365 rpm) 105 % (404 rpm) Airspeed Limits. Never Exceed Speed (VNE) 168 kts IAS For reduction of VNE with altitude and OAT, see RAI-approved Helicopter Flight Manual. Maximum Gear Operating Speed (VLO) Maximum Gear Extended Speed (VLE) Maximum Forward Touchdown Speed 120 kts 120 kts 40 kts IAS IAS IAS Page 3 of 47 H7EU, Rev 32 C.G. Range (Gear Down). Longitudinal Limits (Gear retraction moment is a 4 kgm (347 lb. in) moving CG forward). Longitudinal Station - Inches 120 125 130 135 140 2400 2200 2000 1800 1600 5500 5000 4500 4000 3500 1400 3100 3200 3300 3400 3500 3600 3000 Longitudinal Station - Millimeters CG Range (Gear Down). Lateral Limits - Inches -4 -3 -2 -1 0 1 2 3 4 2500 2000 1500 5500 5000 4500 4000 3500 LEFT -80 -40 0 40 80 RIGHT Lateral Station - Millimeters Empty Weight & CG Range. (None) Maximum Weight. 2450 Kg. (5400 lb) Minimum Crew. One pilot Maximum Passenger. 7: For aircraft conforming with Agusta Report 109-06-01. 1 at sta 1650 mm (65 in) 3 at sta 2485 mm (98 in) 3 at sta 3265 mm (129 in) 0: For aircraft in "green" delivery configuration conforming with Agusta Report 109-06-03. I. Model A109 (cont'd) I. Model A109 (cont'd) 124.7 2450 127.0 129.1 135.3 136.9 138.6 5400 2220 4895 2110 4650 1920 4235 1650 3640 1500 3305 3168 3225 3280 3437 3476 3520 2450 2050 Page 4 of 47 H7EU, Rev 32 Maximum Baggage. 150 Kg. (330 lb) at sta 4920 mm (194 in) Maximum floor loading for baggage compartment: 500 Kg/m2 (102 lb/ft2) Maximum load per tie-down fitting: 91 Kg. (200 lb.) Fuel Capacity. Total : 148.4 U.S. Gal. (559 lit.) in two tanks of 74.2 U.S. Gal. (279.5 lit.) each, at sta. 3650 mm (144.0 in.) Usable : 146 U.S. Gal. (550 lit.) See NOTE 1 for unusable fuel. Oil Capacity Engines. 2 U.S. Gal. (7.7 lit.) each engine, at sta. 3053 mm (136 in) See NOTE 1 for undrainable oil. Maximum Operating Altitude. 4,560 m (15,000 ft) Rotor Blade and Control For rigging information refer to the Model A109 Maintenance Manual. Movements. II. Model A109A (Normal Category Helicopter), approved April 2, 1976. Engines. Two (2) Detroit Diesel Allison Division of General Motors Corporation Model 250-C20B turboshaft engines. Bendix gas producer fuel control DP-N2. Bendix power turbine governor AL-AA1. Fuel. For all temperatures: MIL-T-5624 grade JP-4 ASTM D-1655 Jet B For temperatures above -18ºC (0ºF): MIL-T-5624 grade JP-5 ASTM D-1655 Jet A ASTM D-1655 Jet A1 See NOTE 4 Engine Limits. All engine operation Takeoff (5 minutes) Torque 113% (302 lb.ft) (346 shp) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 105% (53518 rpm) Gas temperature 810ºC (1490ºF) Maximum continuous Torque 113% (302 lb.ft) (346 shp) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 105% (53518 rpm) Gas temperature 738ºC (1360ºF) Single-engine operation (emergency) Takeoff (5 minutes) Torque 131% (350 lb. ft) (400 shp) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 105% (53518 rpm) Gas temperature 810ºC (1490ºF) Maximum continuous Torque 126% (336 lb.ft) (385 shp) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 105% (53518 rpm) Gas temperature 810ºC (1490ºF) (See FAA-approved Helicopter Flight Manual for rpm and temperature transient limits). II. Model A109A (Normal Category Helicopter) (cont'd). Page 5 of 47 H7EU, Rev 32 Rotor Limits. Power off: Maximum 110% (424 rpm) Minimum 90% (346 rpm) Power on: Airspeed Limits. Never exceed speed (VNE) 158 knots IAS (See NOTE 7) For reduction of VNE with altitude and OAT, see RAI-approved Helicopter Flight Manual. CG Range (Gear Down). Longitudinal Limits (Gear retraction moment is 4 kgm (347 lb.in) moving CG forward) Longitudinal Station - Inches 120 125 130 135 140 2600 5732 -6000 2400 2450 5400 -5500 2200 2220 2110 4895 4650 -5000 2000 1800 1920 4235 -4500 -4000 1600 1400 1650 1500 3100 3200 3300 3400 3640 3305 3500 3600 -3500 -3000 Longitudinal Station - Millimeters CG Range (Gear Down). Lateral Limits Lateral Station - Inches -4 -3 -2 -1 0 1 2 3 4 -6000 2600 2500 -5000 2000 -4000 1500 -3000 LEFT -80 -51 -40 0 40 51 80 RIGHT Lateral Station - Millimeters 3305 4520 2050 5400 2450 5732 3168 124.7 3262 128.42 3280 129.1 135.3 3437 3448 135.74 138.6 3520 Maximum 100% (385 rpm) Minimum 95% (365 rpm) Rotor Speed Warning. Low speed 95% (365 rpm) High speed 105% (404 rpm) Maximum Gear Operating Speed (VLO) 120 kts IAS Maximum Gear Extended Speed (VLE) 120 kts IAS Maximum Forward Touchdown Speed 40 kts IAS Page 6 of 47 H7EU, Rev 32 III. Model A109A II (Normal Category Helicopter), approved December 4, 1981. Empty Weight & CG Range. (None) Maximum Weight. 2600 kg (5732 lb.) (See NOTE 7) Minimum Crew. One pilot at Sta. 1630 mm (64 in.) to 1695 mm (67 in.) See NOTE 5. Maximum Passengers. 7: For aircraft conforming with Agusta Report: 109-06-02. 1 at Sta. 1630 mm (64 in) to 1695 mm (67 in) (See NOTE 4). 3 at Sta. 2485 mm (98 in) 3 at Sta. 3265 mm (129 in) 0: For aircraft in "green" delivery configuration conforming with Agusta Report 109-06-07 Maximum Baggage. 150 kg. (330 lb.) at sta 4920 mm (194 in) Maximum floor loading for baggage compartment: 500 kg/m2 (102 lb/ft2) Maximum load per tie-down fitting: 91 kg (200 lb.) Fuel Capacity. Total: 148 U.S. Gal. (559 lit.) in two tanks of 74.2 U.S. Gal. (279.5 lit.) each, at sta 3652 mm (144.0 in.) Usable: 146 U.S. Gal. (550 lit.) See NOTE 1 for unusable fuel. Oil Capacity Engines. 2 U.S. Gal. (7.7 lit.) each engine, at sta 3053 mm (120 in). See NOTE 1 for undrainable oil. Oil Capacity Transmission. 3.2 U.S. Gal. (12 lit.) at sta 3460 mm (136 in) See NOTE 1 for undrainable oil. Maximum Operating Altitude. 2,432 m. (8,000 ft.) See NOTE 7. Rotor Blade and Control Movements. For rigging information refer to the Model A109A/A109AII/A109C Maintenance Manual. Engines. Two (2) Detroit Diesel Allison Division of General Motors Corporation Model 250-C20B or 250-C20R/1 turboshaft engines. Bendix gas producer fuel control DP-N2. Bendix power turbine governor AL-AA1. Fuel. For all temperatures: MIL-T-5624 grade JP-4 ASTM D-1655 Jet B For temperatures above -18ºC (0ºF): MIL-T-5624 grade JP-5 ASTM D-1655 Jet A ASTM D-1655 Jet A1 See NOTE 4 II. Model A109A (Normal Category Helicopter) (cont'd). Page 7 of 47 H7EU, Rev 32 III. Model A109A II (Normal Category Helicopter) (cont'd) Engine Limits. All Engine Operation Takeoff (5 minutes) Torque 97% (323 lb.ft) (370 shp) (-C20R/1 engine) Torque 121% (323 lb.ft) (370 shp) (-C20B engine) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 105% (53518 rpm) Gas temperature 810ºC (1490ºF) Maximum continuous Torque 97% (323 lb.ft) (370 shp) (-C20R/1 engine) Torque 121% (323 lb.ft) (370 shp) (-C20B engine) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 105% (53518 rpm) Gas temperature 738ºC (1360 ºF) (-C20B engine) Gas temperature 752ºC (1358ºF) (-C20R/1 engine) Single-engine operation (emergency) Torque 118% (400 lb.ft) (450 shp) (-C20R/1 engine) Torque 137% (350 lb.ft) (420 shp) (-C20B engine) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 105% (53518 rpm) Gas temperature 810ºC (1490ºF) (See the A109AII Helicopter Flight Manual for rpm and temperature transient limits). Rotor Limits. Power off Maximum 110% (424 rpm) Minimum 90% (346 rpm) Power on Airspeed Limits. Never exceed speed (VNE) 168 knots IAS For reduction of VNE with altitude and OAT, see the A109AII Helicopter Flight Manual. Maximum Gear Operating Speed (VLO) 120 kts IAS Maximum Gear Extended Speed (VLE) 120 kts IAS Maximum Forward Touchdown Speed 40 kts IAS Maximum 100% (385 rpm) Minimum 95% (365 rpm) Rotor Speed Warning. Low speed 95% (365 rpm) High speed 105% (404 rpm) Page 8 of 47 H7EU, Rev 32 III. Model A109A II (Normal Category Helicopter) (cont'd) CG Range (Gear Down). Longitudinal Limits Gear retraction moment is 4 kgm (347 lb.in.) moving CG forward) Longitudinal Station - Inches 120 125 130 135 140 2600 5732 -6000 2400 2450 5400 -5500 2200 2220 2110 4895 4650 -5000 2000 1800 1920 4235 -4500 -4000 1600 1400 1650 1500 3100 3200 3300 3400 3640 3305 3500 3600 -3500 -3000 Longitudinal Station - Millimeters CG Range (Gear Down). Lateral Limits Lateral Station - Inches -4 -3 -2 -1 0 1 2 3 4 -6000 2600 2500 -5000 2000 -4000 1500 LEFT -80 -40 0 40 -3000 80 RIGHT Empty Weight & CG Range (None) Lateral Station - Millimeters Maximum Weight. Minimum Crew. 2600 kg (5732 lb.) One pilot at Sta. 1565 mm (62 in.) to 1630 mm (64 in.) 3305 4520 2050 5400 2450 5732 3.2 3168 124.7 1.6 3262 128.42 3280 129.1 1.6 135.3 3437 3.2 3448 135.74 138.6 3520 Page 9 of 47 H7EU, Rev 32 IV. Model A109C (Normal Category Helicopter), approved August 10, 1989. Maximum Passengers. 7: For aircraft conforming with Agusta Report 109-06-29. 1 at sta. 1565 mm (62 in) to 1630 mm (64 in) 3 at sta. 2420 mm (95 in) Facing FWD or 3 at sta 2455 (97 in) Facing AFT 3 at sta. 3200 mm (126 in) 0: For aircraft in "green" delivery configuration conforming with Agusta Report 109-06-07. See Appendix 15 of required flight manual. Maximum Baggage. 150 kg. (330 lb.) at sta 4920 mm (194 in) Maximum floor loading for baggage compartment: 500 kg/m2 (102 lb/ft2) Maximum load per tie-down fitting: 91 kg (200 lb.) Fuel Capacity. Total: 148.4 U.S. Gal. (559 lit.) in two tanks of 74.2 U.S. Gal. (279.5 lit.) each, at sta 3652 mm (144.0 in.) Usable: 146 U.S. Gal. (550 lit.) See NOTE 1 for unusable fuel See NOTE 9 for fuel capacity with auxiliary fuel tank installation. Oil Capacity Engines. 2 U.S. Gal. (7.7 lit.) each engine, at sta 3053 mm (120 in) See NOTE 1 for undrainable oil. Oil Capacity Altitude. 3.2 U.S. Gal. (12 lit.) at sta 3460 mm (136 in) See NOTE 1 for undrainable oil. Maximum Operating Altitude. 4,560 m. (15,000 ft.) Rotor Blade Control For rigging information refer to the Model A109A/A109AII/A109C Maintenance Movements. Manual. Engines. Two (2) Detroit Diesel Allison Division of General Motors Corporation Model 250-C20R/1 turboshaft engines. Bendix gas producer fuel control DP-N2. Bendix power turbine governor AL-AA1. Fuel. For all temperatures: MIL-T-5624 grade JP-4 ASTM D-1655 Jet B For temperature above -18ºC (0ºF): MIL-T-5624 grade JP-5 ASTM D-1655 Jet A ASTM D-1655 Jet A1 See NOTE 4 III. Model A109A II (Normal Category Helicopter) (cont'd) Page 10 of 47 H7EU, Rev 32 IV. Model A109C (Normal Category Helicopter) (cont'd) Engine Limits. All Engine Operation Takeoff (5 minutes) Torque 104% (345 lb.ft) (395 shp) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 105% (53518 rpm) Gas temperature 810ºC (1490ºF) Maximum Continuous Torque 100% (332 lb.ft) (380 shp) Output shaft speed (N2) 95-100% (5715-6016 rpm) Gas producer speed (N1) 105% (53518 rpm) Gas temperature 752ºC (1385ºF) Single-engine operation (emergency) Torque 118% (400 lb.ft) (450 shp) Output shaft speed (N2) 95-100% (5715-6015 rpm) Gas producer speed (N1) 105% (53518 rpm) Gas temperature 810ºC (1490ºF) (See the A109C Helicopter Flight Manual for rpm and temperature transient limits). Rotor Limits. Power off Maximum 110% (424 rpm) Minimum 90% (346 rpm) Power on Airspeed Limits. Never exceed speed (VNE) 168 knots IAS For reduction of VNE with altitude and OAT, see the A109C Helicopter Flight Manual. Maximum Gear Operating Speed (VLO) 120 kts IAS Maximum Gear Extended Speed (VLE) 120 kts IAS Maximum Forward Touchdown Speed 40 kts IAS Maximum 100% (385 rpm) Minimum 95% (365 rpm) Rotor Speed Limits. Low speed 95% (365 rpm) High speed 105% (404 rpm) Page 11 of 47 H7EU, Rev 32 IV. Model A109C (Normal Category Helicopter) (cont'd) CG Range (Gear Down). Longitudinal Limits Gear retraction moment is 4 kgm (347 lb. in.) moving CG forward Longitudinal Station - Inches 3475 120 125 130 135 140 3245 2800 2600 2400 2200 2409 2720 3500 2600 -6500 -6000 -5500 -5000 2000 1800 1600 1922 3168 1655 1963 -4500 -4000 -3500 3100 3200 3300 3400 3500 3600 Longitudinal Station - Millimeters CG Range (Gear Down). Lateral Limits Lateral Station - Inches -4 -3 -2 -1 0 1 2 3 4 2600 2400 2200 2000 1800 1600 1400 6000 5500 5000 4500 4000 3500 3000 LEFT -80 -40 0 40 80 RIGHT Lateral Station - Millimeters Empty Weight & CG Range. (None) Maximum Weight. 2720 Kg (5997 lb) Minimum Crew. One pilot at Sta. 1565 mm (62 in.) to 1630 mm (64 in.) 2720 2050 Page 12 of 47 H7EU, Rev 32 V. Model A109K2 (Normal Category Helicopter), approved January 15, 1993. Maximum Passengers. 7: For aircraft conforming with Agusta Report 109-06-67 1 at Sta. 1565 mm (62 in) to 1630 mm (64 in) See NOTE 5. 3 at Sta. 2420 mm (95 in) Facing FWD or 3 at Sta 2455 (97 in) Facing AFT 3 at Sta. 3200 mm (126 in) 0: For aircraft in "green" delivery configuration conforming with Agusta Report 109-06-07. See Appendix 15 of required flight manual. Maximum Baggage. 150 kg. (330 lb.) at Sta 4920 mm (194 in) Maximum floor loading for baggage compartment: 500 kg/m2 (102 lb/ft2) Maximum load per tie-down fitting: 91 kg (200 lb.) Fuel Capacity. Total: 148.4 U.S. Gal. (559 lit.) in two tanks of 74.2 U.S. Gal. (279.5 lit.) each, at sta 3652 mm (144.0 in.) Usable: 146 U.S. Gal (550 lit.) See NOTE 1 for unusable fuel. See NOTE 9 for fuel capacity with auxiliary fuel tank installation. Oil Capacity Engines. 2 U.S. Gal. (7.7 lit.) each engine, at sta 3053 mm (120 in) See NOTE 1 for undrainable oil. Oil Capacity Transmission. 3.2 U.S. Gal. (12 lit.) at sta 3460 mm (136 in) See NOTE 1 for undrainable oil. Maximum Operating Altitude. 4,560 m. (15,000 ft.) Rotor Blade Control For rigging information refer to the Model A109A/A109AII/A109C Maintenance Movements. Manual. Engines. Two (2) Turbomeca Model Arriel 1K1 turboshaft engines. Turbomeca Fuel Control Unit 0164348390. Fuel. For all temperatures: MIL-T-5624 grade JP-4, JP-5, ASTM D-1655 Jet A, A1, Jet B, MIL-T-83133 grade JP-8, AIR 3404-F43 (AVCAT) For detailed information see Section 1 of the A109K2 Flight Manual FAA approved. Engine/Xmsn Limits. All Engine Operation Takeoff Torque 100% (900 SHP at N2 100%) Output shaft speed (N2) 100% (6,000 rpm) Gas producer speed (N1) (5 min.) 102% (52,836 rpm) Gas temperature (5 min.) TOT 845ºC (1,553ºF) IV. Model A109C (Normal Category Helicopter) (cont'd) Page 13 of 47 H7EU, Rev 32 V. Model A109K2 (Normal Category Helicopter) (cont'd) Engine Limits (cont'd) Maximum Continuous Torque Output shaft speed (N2) Gas producer speed (N1) Gas temperature Single-engine operation (emergency) (2½ min.) Torque: Output Shaft Speed (N2) Gas Producer Speed (N1) Gas Temperature (TOT) (30 min.) Gas Temperature (TOT) Gas Producer Speed (N1) Maximum Continuous Torque Output Shaft Speed (N2) Gas Temperature 100% (900 SHP at N2 100%) 100% (6,000 rpm) 98.2% (50,868 rpm) 775ºC (1,427ºF) 71.1% (640 SHP at N2 100%) 100% (6000 rpm) 103.1% (53406 rpm) 885ºC (1625ºF) 845ºC (1553ºF) 102% (52,836 rpm) 62.2 (560 SHP at N2 100%) 100% (6000 rpm) 775ºC (1,427ºF) (See the A109K2 Helicopter Flight Manual for rpm and temperature transient limits). Rotor Limits. Rotor Speed Warning. Power off Maximum Minimum Power on Maximum Minimum Low speed High speed 110% (422 rpm) 90% (346 rpm) 100% (384 rpm) 97% (372 rpm) 95% (365 rpm) 105% (403 rpm) Airspeed Limits. CG Range. Never exceed speed (Vne) 152 knots IAS For reduction of Vne with altitude and OAT, see the A109K2 Helicopter Flight Manual. Maximum Forward Touchdown Speed 40 Kts IAS to 2720 Kg 30 Kts IAS over 2720 Kg Longitudinal Limits Longitudinal Station - Inches 120 125 130 135 140 K.G. 2800 2600 2400 2200 2000 1800 2850 2720 2493 2251 2085 6283 5997 5731 4274 6500 6000 5500 5000 LBS. 4500 4000 1600 3100 3200 3300 3400 3500 3600 3500 Longitudinal Station - Millimeters 3277 3297 129.0 129.8 3355 3368 3448 132.0 132.6 135.7 3500 137.8 Page 14 of 47 H7EU, Rev 32 V. Model A109K2 (Normal Category Helicopter) (cont'd) CG Range. (Cont’d) Lateral Limits Lateral Station - Inches -4 -3 -2 -1 0 1 2 3 4 2600 2500 K. G. 2000 6000 5000 LBS. 4000 3000 LEFT -80 -40 0 40 80 RIGHT Lateral Station - Millimeters Empty Weight & CG Range. (None) Maximum Weight. 2,850 Kg (6,283 lb) Minimum Crew. One pilot at Sta 1,565 mm (62 in) to 1,630 mm (64 in) Maximum Passengers. 7 Maximum Baggage. 150 Kg (330 lb) at Sta 4,920 mm (194 in) Maximum floor loading for baggage compartment: 500 Kg/m2 (102 lb/ft2) Maximum load per tie-down fitting: 91 Kg (200 lb) Fuel Capacity. Total Usable: 123.6 US Gal (468 lt) at Sta 3,824 mm (150.56 in) See NOTE 1 for unusable fuel. See NOTE 8 for fuel capacity with auxiliary fuel tank installation. Oil Capacity Engines. 2 US Gal (7.7 lt) each engine, at Sta 3,311 mm (130 in) See NOTE 1 for undrainable oil. Oil Capacity Transmission. 3.2 US Gal (12 lt) at sta 3,441 mm (135 in) See NOTE 1 for undrainable oil. Maximum Operating Altitude. 4,560 m (15,000 ft) Rotor Blade Control Movements For rigging information refer to the Model A109K2 Maintenance Manual. - 3.14 3.14 2850 6283 2450 5401 1939 4274 Page 15 of 47 H7EU, Rev 32 VI. Model A109E (Normal Category Helicopter), approved August 26, 1996. Engines. Two (2) Pratt & Whitney Canada Inc. PW206C turboshaft engines. FADEC control engines Two (2) Turbomeca Arrius 2K1: TM 2K1 turboshaft engines. FADEC control engines P/N 70 EMK 00520 Fuel PW 206C. For all temperatures: ASTM D-1655 Jet A, A1, A2 Jet B. Fuel TM 2K1. ASTM D-1655 Jet A, A1 Military specification (only for reference) MIL-T-5624 grade JP-4, JP-5, MIL-T-83133 grade JP-8, For detailed information see Section I of the applicable FAA approved A109E Flight Manual. Engine/Xmsn Limits. All Engine Operation (PW206C engine) Takeoff Torque 122% (549 SHP at N2 100%) Output shaft speed (N2) 102% (6120 rpm) Gas producer speed (N1) 98.7% (57250 rpm) Gas temperature (5 min.) TOT 863ºC (1585.4ºF) Maximum Continuous Torque 122% (549 SHP at N2 100%) Output shaft speed (N2) 100% (6060 rpm) Gas producer speed (N1) 97.4% (56500 rpm) Gas temperature 820ºC (1508ºF) Single-engine operation (emergency) 2½ min. Torque 142% (640 SHP at N2 100%) Output Shaft Speed (N2) 102% (6120 rpm) Gas Producer Speed (N1) 102.4% (59400 rpm) Gas Temperature (TOT) 930ºC (1706ºF) Maximum Continuous Torque 138% (622 SHP at N2 100%) Output shaft speed (N2) 100% (6060 rpm) Gas producer speed (N1) 100.4% (58250 rpm) Gas temperature 885ºC (1625ºF) A109E helicopters that entered service prior to January 29, 1998 have a torque meter scale defined in Appendix 13 of the Rotorcraft Flight Manual. (TM 2K1 engine) All Engine Operation Takeoff Torque 142% (640 SHP at N2 100%) Output shaft speed (N2) 102% (6120 rpm) Gas producer (N1) 0% Gas producer speed (N1) 54706 rpm) Gas temperature (5 min.) TOT905ºC (1661.4ºF) Maximum Continuous Torque 127% (573 SHP at N2 100%) Output shaft speed (N2) 100% (6060 rpm) Gas producer (N1) -2.4% Gas producer speed (N1) 53406 rpm Gas temperature 866ºC (1521ºF) Page 16 of 47 H7EU, Rev 32 VI. Model A109E (Normal Category Helicopter) (cont’d) Engine/Xmsn Limits. (cont'd) Single-engine operation (emergency) 2½ min. Torque 155% (700 SHP at N2 100%) Output shaft speed (N2) 102% (6120 rpm) Gas producer (N1) +2.6% Gas producer speed (N1) 56113 rpm Gas temperature 957ºC (1521ºF) Maximum Continuous Torque 142% (640 SHP at N2 100%) Output shaft speed (N2) 100% (6060 rpm)