# TCDS H7EU: Leonardo S.p.A. - Type: Type certificate data sheet - Status: Current - Holder: Leonardo S.p.A. - Revision: 32 - Revised: July 6, 2026 - Product: Aircraft, Rotorcraft - Certification basis: Part 29, Part 21 - Registered aircraft: 350, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/78/76/7876612ea67d5d946a450da8bece2bee136f8f7a305a2c58f9c4982710ee2b5f - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID141710484820260707164925.0001 - Page: https://openairdocs.org/tcds/H7EU ## Models (10) As the data sheet lists them. - AW119 MKII - A119 - A109 - A109A - A109E - AW109SP - A109K2 - A109A II - A109S - A109C ## What the data sheet says Some pages are OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text 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) Gas producer (N1) 0% Gas producer speed (N1) 54706 rpm Gas temperature 905ºC (1521ºF) Transmission Limits. All Engine Operation (torque Tq) Maximum Continuous 100% (450 SHP) Transient (6 second) 110% (495 SHP) Single Engine Operation (torque Tq) Maximum Continuous 124% (558 SHP) 2 ½ minute 142% (640 SHP) Transient (6 seconds) 156% (702 SHP) Rotor Limits. Power off Maximum 110% (422 rpm) Minimum 90% (346 rpm) Power on all engine operative Maximum 102% (394 rpm) Minimum 99% (380 rpm) Power on single engine (OEI) Maximum Minimum 102% (394 rpm) 90% (346 rpm) Rotor Speed Warning. Low speed Power On - Maximum 95.5% (367 rpm) Power Off - Minimum High speed 89.5% (344 rpm) 105.5% (405 rpm) Airspeed Limits. Never exceed speed (Vne) 168 knots IAS power on 128 knots IAS power off/OEI For reduction of Vne with altitude and OAT, see the applicable FAA approved A109E Helicopter Flight Manual. Maximum Forward Touchdown Speed 40 Kts IAS Page 17 of 47 H7EU, Rev 32 VI. Model A109E (Normal Category Helicopter) (cont’d) 50 4078 1850 5401 2450 6283 28 6283 2850 126.7 127.7 - 1.57 132.0 1.57 137.7 139.7 C.G. Range Longitudinal limits Longitudinal Station - Inches 125 130 135 140 145 3000 6500 2800 2600 2720 6000 Gross Weight kg 2400 2200 5500 5000 Gross Weight lbs 2000 2100 4500 Minimum 1800 ght 1850 4078 4000 1600 3500 3200 3300 3400 3500 3600 3700 Longitudinal Station - Millimeters Lateral limits Lateral Station - Inches -4 -3 -2 -1 0 1 2 3 4 6500 6000 5500 Lbs. 5000 4500 4000 LEFT -80 -40 0 40 3500 80 RIGHT Lateral Station - Millimeters flying wei 1 5997 573 3220 3245 - 80 3355 3498 80 3550 3000 2800 2600 Kg 2400 2200 2000 1800 1600 Page 18 of 47 H7EU, Rev 32 VII. Model A119 (Normal Category Helicopter), approved April 28, 2000. 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 5,300 mm (209 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: 157 US Gal (595 lt) See NOTE 1 for unusable fuel. Oil Capacity Engines. PW 206C 1.35 US Gal (5.12 lt) each engine See NOTE 1 for undrainable oil. Oil Capacity Engines. TM 2K1 1.13 US Gal (4.3 lt) each engine See NOTE 1 for undrainable oil. Oil Capacity Transmission. 2.9 US Gal (11 lt) See NOTE 1 for undrainable oil. Maximum Operating Altitude. PW 206C 15,000 ft (4,560 m) TM 2K1 20,000 ft (6,096 m) Rotor Blade Control Movements For rigging information refer to the Model A109E Maintenance Manual. Engine. One (1) Pratt & Whitney Canada Inc. PT6B-37A Turboshaft engine Build Specification No. 1017 (for helicopters not equipped with Integrated Display System) or Build Specification No. 1142 (for helicopters equipped with Integrated Display System) Electronic Engine Control (EEC) Fuel. For all temperatures: ASTM D-1655 Jet A, Jet A-1, Jet A-2 Military specification (only for reference): MIL-T-5624 grade JP-5, MIL-T-83133 grade JP-8 For detailed information: see Section 1 of the A119 Flight Manual - FAA approved Engine/Xmsn Limits. Takeoff Torque 108.5% (900 SHP at N2 100%) Output Shaft Speed (N2) 101% (4416 rpm) Gas Producer Speed (N1) 103.2% (39300 rpm) Gas Temperature 5 min. (ITT) 810°C (1490.4 °F) Maximum Continuous Torque 100% (830 SHP at N2 102%) Output Shaft Speed (N2) 101% (4416 rpm) Gas Producer Speed (N1) 100.1% (38100 rpm) Gas Temperature (ITT) 755°C (1391 °F) VI. Model A109E (Normal Category Helicopter) (cont’d) Page 19 of 47 H7EU, Rev 32 VII. Model A119 (Normal Category Helicopter) (cont’d) Rotor Limits. Power off Maximum 110% (422 rpm) Minimum 90% (346 rpm) Power on Maximum 101% (388 rpm) 103% (396 rpm) with torque <50% Minimum 95% (365 rpm) Rotor Speed Warning. Low speed 96% (369 rpm) High speed 108% (415 rpm) Airspeed Limits. Never exceed speed (Vne) 152 knots IAS power on For reduction of the Vne with altitude and OAT, see the A119 Rotorcraft Flight Manual. C.G. Range. Longitudinal Limits. Page 20 of 47 H7EU, Rev 32 VII. Model A119 (Normal Category Helicopter) Cont’d CG Range. Lateral Limits Empty Weight & CG Range. (None) Maximum Weight. 2,720 Kg (5,997 lb) Minimum Crew. One pilot between STA 1,565 mm (62 in) and STA 1,630 mm (64 in) Maximum Passengers. 7 Maximum Baggage. 150 Kg (330 lb) between STA 4,880 (192 in) and STA 6,430 mm (253 in) Maximum floor loading for baggage compartment: 500 Kg/m2 (102 lb/ft2). Fuel Capacity. Total Usable: 157 US Gal (595 lt) See NOTE 1 for unusable fuel See NOTE 8 for fuel capacity with supplementary fuel tank installation. Oil Capacity Engine. 2.76 US Gal (10.45 lt) See NOTE 1 for undrainable oil. Oil Capacity Transmission. 2.72 US Gal (10.3 lt) See NOTE 1 for undrainable oil. Maximum Operating Altitude. 4,572 m (15,000 ft) Rotor Blade Control Movements. For rigging information refer to the Model A119 Maintenance Manual. Page 21 of 47 H7EU, Rev 32 VIII. Model A109S (Normal Category Helicopter), approved July 20, 2006. Engines. Two (2) Pratt & Whitney Canada Inc. PW207C turboshaft engines. FADEC control engines Fuel PW 207C. For all temperatures: ASTM D-1655 Jet A, A1 Military specification (only for reference) MIL-T-5624 grade , JP-5, MIL-T-83133 grade JP-8, For detailed information see Section I of the applicable FAA approved A109S / A109S Trekker Rotorcraft Flight Manual. Emergency Fuel Refer to FAA approved RFM Section 1, for detailed information Engine/Xmsn Limits. All Engine Operation PW207C engine) Takeoff Torque 125% (562 SHP at N2 100%) Output shaft speed (N2) 102% (6120 rpm) Gas producer speed (N1) 99.7% (57826 rpm) Gas temperature (5 min.) TOT 900ºC (1652ºF) Maximum Continuous Torque 125% (562 SHP at N2 100%) Output shaft speed (N2) 101% (6060 rpm) Gas producer speed (N1) 97.1% (56318 rpm) Gas temperature (TOT) 840ºC (1544ºF) Single-engine operation (emergency) 2½ min Torque 162% (730 SHP at N2 100%) Output Shaft Speed (N2) 102% (6120 rpm) Gas Producer Speed (N1) 103% (59740 rpm) Gas Temperature (TOT) 970ºC (1778ºF) Transmission Limits. Maximum Continuous Torque 141% (633 SHP at N2 100%) Output shaft speed (N2) 101% (6060 rpm) Gas producer speed (N1) 99.7% (57826 rpm) Gas temperature (TOT) 900ºC (1652ºF) All Engine Operation (torque Tq) Maximum Continuous 100% (900 SHP) Take off (5 minutes) 107% (960 SHP) Transient (6 second) 110% (990 SHP) Single Engine Operation (torque Tq) Maximum Continuous 133% (600 SHP) 2 ½ minute 162% (730 SHP) Transient (6 seconds) 173% (780 SHP) Rotor Limits. Power off Maximum 110% (422 rpm) Minimum 95% (365 rpm) Power on all engine operative Maximum 102% (394 pm) Minimum 99% (380 rpm) Power on single engine (OEI) Maximum 102% (394 rpm) Minimum 90% (346 rpm) Page 22 of 47 H7EU, Rev 32 VIII. Model A109S (Normal Category Helicopter) (cont'd) Rotor Speed Warning. Low speed Power On – Maximum Power Off – Minimum 95.5% (367 rpm) 94.5% (344 rpm) High speed Power On Power Off 105.5% (405 rpm) 111% (428 rpm) A109S Airspeed Limits. Never exceed speed (Vne) 168 knots IAS power on 128 knots IAS power off/OEI For reduction of Vne with altitude and OAT, see the applicable FAA approved A109S Rotorcraft Flight Manual. Refer to FAA approved RFM Section 1, for detailed information on other VNE limits and other speed limitations A109S Trekker Airspeed Limits. Never exceed speed (Vne) 160 knots IAS power on 120 knots IAS power off/OEI For reduction of Vne with altitude and OAT, see the applicable FAA approved A109S Trekker Rotorcraft Flight Manual. Refer to FAA approved RFM Section 1, for detailed information on other VNE limits and other speed limitations C.G. Range A109S Longitudinal limits (mm) Page 23 of 47 HEU, Rev 32 VIII. Model A109S (Normal Category Helicopter) (cont'd) A109S Lateral (mm) 3400 3200 3175 3175 3000 Gross Weight (kg) 2800 2600 2450 C.L 2450 2400 2200 2050 2050 2000 -80 1800 1600 - 100 -60 -20 20 60 100 Lateral Station (mm) A109S Longitudinal limits (inch) 7500 131,1 135,0 7000 17000 127,9 6500 6415 6548 Gross Weight (Ibs) 6000 5500 5225 5000 127,0 4500 | 4519 134,4 138,5 4000 3500 - 126 128 130 132 134 136 138 140 Longitudinal Station (in) Page 24 of 47 HEU, Rev 32 VIII. Model A109S (Normal Category Helicopter) (cont'd) A109S Lateral (inch) 7500 7000 7000 6500 6000 -3,1 5500 5401 5401 5000 4500 • 4519 4519 -3,1 4000 3500 -4,00 -3,00 -2,00 -1,00 0,00 1,00 2,00 3,00 4,00 Lateral Station (in) A109S with Trekker Kit P/N 109G0000F01 Longitudinal (mm) Longitudinal GW/OG envelope 3400 3300 3330 3430 3200 3175 3100 3000 2970 2900 2910 = 2800 3249 oss Weight 2700 2600 2500 2400 2370 2300 2200 2100 2050 2000 3415 3520 1900 1800 3200 3250 3300 3350 3400 3450 3500 3550 STA [mm ] Page 25 of 47 HEU, Rev 32 A109S with Trekker Kit P/N 109G0000F01 Longitudinal (in) Longitudinal GW/CG envelope 7500 131,1 7000 7000 6500 18410 cas Weight [Ibs] 127,9 6000 6500 5000 4500 4515 |134,4 138,6 4000 124,00 126,00 128,00 130,00 132,00 134,00 136,00 139,00 140,00 STA [in] A109S with Trekker Kit P/N 109G0000F01 Lateral (mm) Lateral GW/CG envelope 3400 3300 -40 3200 3175 3100 3000 2900 2800 2700 2800 2500 2400 2450 2450 2300 2200 2100 2050 -во - 80,00 -40,00 -20,00 0,00 20,00 40,00 60,00 BL [mm] Page 26 of 47 H7EU, Rev 32 A109S with Trekker Kit P/N 109G0000F01 Lateral (in) Empty Weight & CG Range. (None) Maximum Take Off Weight. 3,175 Kg (7,000 lb) Minimum Crew. One pilot at Sta 1,328 mm (52,3 in) to 1,404 mm (55,3 in) The pilot must be seated in the right seat Maximum Passengers. 7 Maximum Baggage. 120 Kg (264 lb) at Sta 4,880 mm to 6430 mm ref.RFM for baggage load distribution Maximum floor loading for baggage compartment: 500 Kg/m2 (102 b/ft2) Maximum load per tie-down fitting: 91 Kg (200 lb) Fuel Capacity. Total Usable: 148.5 US Gal (562 lt) See NOTE 1 for unusable fuel. Oil Capacity Engines. PW 207C 1.38 US Gal (5.25 lt) for each engine See NOTE 1 for undrainable oil. Oil Capacity Transmission. 3,09 US Gal (11,7 lt) Maximum Operating Altitude. PW 207C See NOTE 1 for undrainable oil. 20,000 ft (6,096 m) Blade Control Movements Main -1° / +12° Tail RH pedal –7° LH pedal + 24° For rigging information refer to the Maintenance Manual Page 27 of 47 H7EU, Rev 32 IX. Model AW119 MKII (Normal Category Helicopter), approved October 22, 2007. Engine. One (1) Pratt & Whitney Canada Inc. PT6B-37A Turboshaft engine Build Specification No. 1242 Electronic Engine Control (EEC) Fuel. For all temperatures: ASTM D-1655 Jet A, Jet A-1 Military specification (only for reference): MIL-T-5624 grade JP-5, MIL-T-83133 grade JP-8 For detailed information: see Section 1 of the AW119 MKII RFM - FAA approved Engine/Xmsn Limits. Takeoff (5 min) Torque 108.5% (917 SHP at N2 102%) Output Shaft Speed (N2) 102% (4460 rpm) Note: Operation up to N2 103% is permitted Gas Producer Speed (N1) 103.2% (39300 rpm) Gas Temperature (ITT) 810°C (1490.4 °F) Maximum Continuous Torque 100% (847 SHP at N2 102%) Output Shaft Speed (N2) 102% (4460 rpm) Note: Operation up to N2 103% is permitted Gas Producer Speed (N1) 100.1% (38100 rpm) Gas Temperature (ITT) 755°C (1391 °F) Rotor Limits. Power off Maximum 110% (422 rpm) Minimum 90% (346 rpm) Power on Maximum 103% (396 rpm) Minimum 95% (365 rpm) Rotor Speed Warning. Low speed 96% (369 rpm) High speed 108% (415 rpm) Airspeed Limits. Never exceed speed (Vne) 152 knots IAS power on For reduction of the Vne with altitude and OAT, see the AW119 MKII Rotorcraft Flight Manual. Page 28 of 47 HEU, Rev 32 IX. Model AW119 MKII (Normal Category Helicopter) Cont'd C.G. Range. Longitudinal Limits. 3200 3000 2800 2600 Gross Weight (kg) |2531 - 2400 2200 2160— 2000 3284 1800 - 1812- Minimu 725 flyin weight 3457 1600 [3528 3580) 1400 3200 3300 3400 3500 3600 3700 Longitudinal Station (mm) CG Range. Lateral Limits 3200 3000 2800 2600 Gross Weight (kg) 2450 2450 2400 2200 2000 1800 Minimum 1725- - 1725 flying weight 1600 1400 -100-80-60-40-20 0 20 40 60 80 100 Lateral Station (mm) Empty Weight & CG Range. (None) Maximum Weight. 2,850 Kg (6283 lb) Minimum Crew. One pilot between STA 1,565 mm (62 in) and STA 1,630 mm (64 in) Maximum Passengers. 7 Page 29 of 47 H7EU, Rev 32 X. Model AW109SP (Normal Category Helicopter), approved October 14, 2010. Maximum Baggage. 150 Kg (330 lb) between STA 4,880 (192 in) and STA 6,430 mm (253 in) Maximum floor loading for baggage compartment: 500 Kg/m2 (102 lb/ft2). Fuel Capacity. Total Usable: 157 US Gal (595 lt) See NOTE 1 for unusable fuel See NOTE 8 for fuel capacity with supplementary fuel tank installation. Oil Capacity Engine. 2.76 US Gal (10.45 lt) See NOTE 1 for undrainable oil. Oil Capacity Transmission. 2.72 US Gal (10.3 lt) See NOTE 1 for undrainable oil. Maximum Operating Altitude. 4,572 m (15,000 ft) Rotor Blade Control Movements. For rigging information refer to the A119/AW119 MKII Maintenance Manual. Engines. Two (2) Pratt & Whitney Canada Inc. PW207C turboshaft engines. FADEC control engines Fuel PW 207C. For all temperatures: ASTM D-1655 Jet A, A1 Military specification (only for reference) MIL-T-5624 grade , JP-5, MIL-T-83133 grade JP-8, For detailed information see Section I of the applicable FAA approved AW109SP Rotorcraft Flight Manual. Emergency Fuel Refer to FAA approved RFM Section 1, for detailed information Engine/Xmsn Limits. All Engine Operation PW207C engine) Takeoff Torque 125% (562 SHP at N2 100%) Output shaft speed (N2) 102% (6120 rpm) Gas producer speed (N1) 99.7% (57826 rpm) Gas temperature (5 min.) TOT 900ºC (1652ºF) Maximum Continuous Torque 125% (562 SHP at N2 100%) Output shaft speed (N2) 101% (6060 rpm) Gas producer speed (N1) 97.1% (56318 rpm) Gas temperature (TOT) 840ºC (1544ºF) Single-engine operation (emergency) 2½ min Torque 162% (730 SHP at N2 100%) Output Shaft Speed (N2) 102% (6120 rpm) Gas Producer Speed (N1) 103% (59740 rpm) Gas Temperature (TOT) 970ºC (1778ºF) Maximum Continuous Torque 141% (633 SHP at N2 100%) Output shaft speed (N2) 101% (6060 rpm) Gas producer speed (N1) 99.7% (57826 rpm) Gas temperature (TOT) 900ºC (1652ºF) IX. Model AW119 MKII (Normal Category Helicopter) Cont’d Page 30 of 47 H7EU, Rev 32 X. Model AW109SP (Normal Category Helicopter) (cont'd) Transmission Limits. All Engine Operation (torque Tq) Maximum Continuous Take off (5 minutes) Transient (6 second) 100% (900 SHP) 107% (960 SHP) 110% (990 SHP) Single Engine Operation (torque Tq) Maximum Continuous 2 ½ minute Transient (6 seconds) Rotor Limits. Power off Maximum Minimum 133% (600 SHP) 162% (730 SHP) 173% (780 SHP) 110% (422 rpm) 95% (365 rpm) Power on all engine operative Maximum Minimum 102% (394 pm) 99% (380 rpm) Power on single engine (OEI) Maximum Minimum 102% (394 rpm) 90% (346 rpm) Rotor Speed Warning. Low speed Power On – Maximum Power Off – Minimum 95.5% (367 rpm) 94.5% (344 rpm) High speed Power On Power Off 105.5% (405 rpm) 111% (428 rpm) Airspeed Limits. Never exceed speed (Vne) 168 knots IAS power on 128 knots IAS power off/OEI For reduction of Vne with altitude and OAT, see the applicable FAA approved AW109SP Rotorcraft Flight Manual. Refer to FAA approved RFM Section 1 for detailed information on other VNE limits Ground Speed Limits Maximum take off and Touchdown Speed on concrete or even surfaces: 40 Kts IAS Maximum take off and Touchdown Speed on unprepared or uneven surfaces: 20 Kts IAS Refer to FAA approved RFM Section 1 for detailed information Page 31 of 47 H7EU, Rev 32 X. Model AW109SP (Normal Category Helicopter) (cont'd) C.G. Range Longitudinal limits (mm) 3300 3000 2700 Longitudinal Envelope AW109SP 2400 2100 1800 3150.00 3200.00 3250.00 3300.00 3350.00 3400.00 3450.00 3500.00 3550.00 Longitudinal station (mm) STA 3330 3175 kg STA 3430 2970 kg STA 3249 2910 kg STA 3225 2370 kg STA 3444 2050 kg STA 3520 Weight (Kg) Page 32 of 47 H7EU, Rev 32 X. Model AW109SP (Normal Category Helicopter) (cont'd) Lateral (mm) 3400 3200 3000 2800 2600 2400 2200 2000 Lateral Envelope AW109SP 1800 -100.00 -80.00 -60.00 -40.00 -20.00 0.00 20.00 40.00 60.00 80.00 100.00 Lateral station (mm) STA -40 3175 kg STA 40 2450 kg 2450 kg STA -80 2050 kg STA 80 Weight (Kg) Page 33 of 47 H7EU, Rev 32 X. Model AW109SP (Normal Category Helicopter) (cont'd) Longitudinal limits (inch) 7300 Longitudinal Envelope AW109SP 7000 6700 6400 6100 5800 5500 5200 4900 4600 4300 4000 124.00 126.00 128.00 130.00 132.00 134.00 136.00 138.00 140.00 Longitudinal station (inches) STA 131.10 7000 lbs STA 135.03 6548 lbs STA 127.91 6415 lbs STA 126.96 5225 lbs STA 135.59 4519 lbs STA 138.58 Weight (Lbs) Page 34 of 47 H7EU, Rev 32 X. Model AW109SP (Normal Category Helicopter) (cont'd) Lateral (inch) 7500 7000 6500 6000 5500 5000 4500 4000 - Lateral Envelope AW109SP STA -1.6 7000 lbs STA 1.6 5401 lbs 5401 lbs STA -3.1 4519 lbs STA 3.1 Weight (lbs) -4.00 3.00 -2.00 -1.00 0.00 1.00 2.00 3.00 4.00 Lateral station (inches) Empty Weight & CG Range. (None) Maximum Take Off Weight. 3,175 Kg (7,000 lb) Minimum Crew. One pilot at Sta 1,328 mm (52,3 in) to 1,404 mm (55,3 in) The pilot must be seated in the right seat Maximum Passengers. 7 Maximum Baggage. 120 Kg (264 lb) at Sta 4,880 mm to 6430 mm ref .RFM for baggage load distribution Maximum floor loading for baggage compartment: 500 Kg/m2 (102 b/ft2) Maximum load per tie-down fitting: 91 Kg (200 lb) Fuel Capacity. Total Usable: 148.5 US Gal (562 lt). See NOTE 1 for unusable fuel. Oil Capacity Engines. PW 207C 1.38 US Gal (5.25 lt) for each engine. See NOTE 1 for undrainable oil. Oil Capacity Transmission. Maximum Operating Altitude. 3,09 US Gal (11,7 lt). See NOTE 1 for undrainable oil. PW 207C 20,000 ft (6,096 m) Blade Control Movements Main -1° / +12° Tail RH pedal –7° LH pedal + 24° For rigging information refer to the Model AW109SP Maintenance Manual Page 35 of 47 H7EU, Rev 32 DATA PERTINENT TO ALL MODELS Datum. Longitudinal station 0 (datum) is 1835 mm (72 in) forward of the front jack point. For the A119 and AW119 MKII, longitudinal station 0 (datum) is 1785 mm (70.3 in) forward of the front jack point. For the A109S and AW109SP, longitudinal station 0 (datum) is 1635 mm (64,37 in) forward of the front jack point. For the A109S equipped with Trekker Kit P/N 109G0000F01, longitudinal station 0 (datum) is 1580mm (62.2 in) forward of the front jack point. Lateral station 0 (datum) is ± 450 mm (± 18 in) inboard of each main jack point and coincides with the rotorcraft longitudinal plane of symmetry. Leveling Means. A109, A109A, A109AII, A109C, A109K2 and A119 plumb line from ceiling reference point to index plate on floor of passenger cabin. For A109E, A109S, A109S with Trekker Kit P/N 109G0000F01 and AW109SP the leveling is performed by a water level put on the datum plate located on the cabin roof, RH side. AW119MKII uses either one of the two leveling methods described above. Serial Numbers Eligible. A ENTE NAZIONALE AVIAZIONE CIVILE (ENAC) Certificate of Airworthiness for Export endorsed as noted under import requirements must be submitted for each individual rotorcraft for which application for certification is made. For the A109: the eligible Serial Numbers are from 7106 to 7109. For the A109A: the eligible Serial Numbers are from 7110 to 7114 (P/N assy 109-9000-01-11), from 7115 to 7125 (P/N Assy 109-9000-01- 15), from 7126 to 7135 (P/N Assy 109-9000-01-19), from 7136 to 7165 (P/N Assy 109-9000-01-23), from 7166 to 7255 (P/N Assy 109-9000-01-27). For the A109A II: the eligible Serial Numbers are from 7256 to 7600. For the A109C: the eligible Serial Numbers are from 7601 to 7800. For the A109K2: the eligible Serial Numbers are from 10001 to 10100. For the A109E: the eligible Serial Numbers are from 11001 to 11999. For the A119: the eligible Serial Numbers are from 14003 to 14700. (See NOTE 18) For the AW119 MKII: the eligible Serial Numbers are from 14701 to 14900. (See NOTE 18) For the AW119MKII equipped with G1000H Kit P/N 109G4600F01-101 and G1000H NXi Kit P/N 10G4600F01-201: the eligible Serial Numbers are from 14901 to 15999. (See NOTE 18) For the A109S: the eligible Serial Numbers are 22001, 22003 through 22087, 22089 through 22200. For the A109S equipped with Trekker Kit P/N 109G0000F01: the eligible Serial Numbers are 22002, 22088, 22701 to 22999. For the AW109SP the eligible Serial Numbers are S/N 22201, 22203, from 22214 to 22362, 22364 and subs. Certification Basis. FAR 21.29 and FAR Part 27 dated February 1, 1965, including Amendments 27-1 through 27-8. FAR Part 29 dated February 1, 1965, para. 29.903(b), for Category “A” engine isolation. Special Conditions for Agusta Model A109 helicopter No. 27-54-EU-17, issued on June 26, 1973. Equivalent safety in lieu of compliance shown for: -FAR 27.1189, re shutoff means -FAR 27.1305(d), re fuel quantity indicator for A109A up to S/N 7165. -FAR 27.927(c) at amendment 27-12 elected by the applicant For the Model A109K2, in addition to the above: -27.25 Amendment 11 -27.79 Amendment 21 -27.143 Amendment 21 -27.865 Amendment 11 -27.923 Amendment 12 (for reference only) -27.939 Amendment 11 -27.951 Amendment 9 Page 36 of 47 H7EU, Rev 32 -27.1093 Amendment 20 For the Model A109E in addition to the above: -27.2 Amendment 28 -27.21 Amendment 21 -27.45 Amendment 21 -27.71 Amendment 21 -27.141 Amendment 21 -27.175 Amendment 21 -27.177 Amendment 21 -27.401 Amendment 27 -27.610 Amendment 21 -27.901 Amendment 23 -27.903 Amendment 23 -27.927 Amendment 23 -27.954 Amendment 23 -27.1091 Amendment 23 -27.1189 Amendment 23 -27.1305 Amendment 23 Certification Basis (Cont’d). -27.1321 Amendment 13 -27.1322 Amendment 11 -27.1323 Amendment 13 -27.1325 Amendment 13 -27.1401 Amendment 10 -27.1505 Amendment 21 -27.1519 Amendment 21 -27.1521 Amendment 23 -27.1527 Amendment 14 -27.1529 Amendment 18 -27.1549 Amendment 23 -27.1555 Amendment 21 -27.1557 Amendment 11 -27.1581 Amendment 14 -27.1583 Amendment 16 -27.1585 Amendment 21 -27.1587 Amendment 21 Special conditions for Agusta Models A109D and A109E helicopters, High Intensity Radiated Fields No. 27-ASW-3 issued on June 13, 1996. Equivalent safety in lieu of compliance shown for: FAR 27.175(c), re static longitudinal stability. For the Model A119 in addition to the above: - FAR 27.29, Amdt. 14 - FAR 27.33, Amdt. 14 - FAR 27.65, Amdt. 33 - FAR 27.71, Amdt. 21 - FAR 27.151, Amdt. 21 - FAR 27.161, Amdt. 21 - FAR 27.173, Amdt. 21 - FAR 27.307, Amdt. 26 - FAR 27.321, Amdt. 11 - FAR 27.337, Amdt. 26 - FAR 27.339, Amdt. 11 - FAR 27.351, Amdt. 26 - FAR 27.361, Amdt. 23 - FAR 27.391, Amdt. 26 - FAR 27.395, Amdt. 26 - FAR 27.397, Amdt. 11 - FAR 27.427, Amdt. 27 - FAR 27.501, Amdt. 26 - FAR 27.571, Amdt. 26 - FAR 27.602, Amdt. 38 - FAR 27.603, Amdt. 16 - FAR 27.613, Amdt. 26 Page 37 of 47 H7EU, Rev 32 Certification Basis (Cont’d). - FAR 27.663, Amdt. 26 - FAR 27.672, Amdt. 21 - FAR 27.727, Amdt. 26 - FAR 27.779, Amdt. 21 - FAR 27.783, Amdt. 26 - FAR 27.807, Amdt. 26 - FAR 27.863, Amdt. 16 - FAR 27.917, Amdt. 11 - FAR 27.923, Amdt. 29 - FAR 27.955, Amdt. 23 - FAR 27.967, Amdt. 30 - FAR 27.975, Amdt. 30 - FAR 27.977, Amdt. 11 - FAR 27.997, Amdt. 23 - FAR 27.1027, Amdt. 23 - FAR 27.1041, Amdt. 23 - FAR 27.1043, Amdt. 14 - FAR 27.1045, Amdt. 23 - FAR 27.1141, Amdt. 33 - FAR 27.1143, Amdt. 29 - FAR 27.1145, Amdt. 12 - FAR 27.1193, Amdt. 23 - FAR 27.1327, Amdt. 13 - FAR 27.1337, Amdt. 23 - FAR 27.1411, Amdt. 11 - FAR 27.1501, Amdt. 14 - FAR 27.1525, Amdt. 21 - FAR 27.1545, Amdt. 16 - FAR 27.1547, Amdt. 13 - FAR 27.1559, Amdt. 21 - 27 Appendix A, Amdt. 24 For the Model A109S: - FAR Part 21.29 and FAR Part 27 as quoted in the FAA TCDS H7EU Revision 19 for unchanged area and FAR Part 27 Amendment 27-1 through 27-40 for the new or changed parts with respect to the A109E identified in the Agusta document n° 109-01- 182 rev B; - the exceptions of 27.863. - Appendix A to Part 27 of Amendment 27-24. - Appendix B to Part 27 of Amendment 27-19 - FAR 36, Appendix H, Amendment 36-1 through the amendment in effect at the time of conducting the noise tests. - Special Condition for High Intensity Radiated Field (HIRF), No. 27-ASW-3, issued on June 13, 1996. - Category A Operations Appendix C to FAR 27. - The main differences between the A109S and the A109E are as follows • Maximum weight increase from 2850 kg to 3175 kg. • Stretched passenger cabin. • New tail rotor with composite blades. • Engine PW207C with new rating. • New main and nose landing gear. • New engine and transmission oil cooler components. • Engine control cable and engine control lever electronic control. • Modified two FFC levers. • Modified fuel quantity probe and computing unit for new fuel tanks. • Updated new limits in Integrated Display System (IDS). • Aircraft Battery relocated. • New ICS NAT. • New Main rotor P/N 109-0112-01-103. • New COM/NAV. • New pilot seats. • Modified passenger seats installation and fuel system. • Installed new interior. For the A109S equipped with Trekker Kit P/N 109G0000F001: Page 38 of 47 H7EU, Rev 32 - A109S Certification Basis for the areas not affected by the Trekker Kit installation - FAR 27 Amdt. Up to 47 for the changed areas as identified in Leonardo document n° 109G0274A001. - Special Condition: HIRF Protection according to JAA Interim Policy, Paper No. INT/POL/27&29/1 Issue 3, equivalent to FAR 27.1317 Amdt.42 - Equivalent Level of Safety to 14 CFR §27.1305, §27.1521, §27.1549, §27.1309(c), §29.1309(b)(2)(i) and (d): Power Index Indicator. For the Model AW109SP - FAR Part 21.29 and FAR Part 27 as quoted in the FAA TCDS H7EU rev 23 for unchanged area and FAR Part 27 Amendment 27-1 through 27-42 for the new or changed parts with respect to the A109S identified in the Agusta document n° 109G0000N062 rev. A and 109G0000N091 rev. B; - the exceptions of 27.863. - Appendix A to Part 27 of Amendment 27-24. - Appendix B to Part 27 of Amendment 27-19 - Category A Operations Appendix C to Part 27 - HIRF Appendix D to part 27.1317 - FAR 36, Appendix H, Amendment 36-1 through the amendment in effect at the time of conducting the noise tests. -The main differences between the AW109SP and the A109S are as follows • New main structure made of both metallic and composite material • New FQGS (Fuel quantity gauging system) • New Starter Generator (200 amp) • New AFCS (New design, 4-channels, digital AFCS, using AHRS, RAD Alt, ADU and NAV systems as input equipment, interfaced with cockpit) • New Avionics (Digital system, integrated with Digital Audio Communication System, 4 EFIS display with synthetic vision system and FMS) The A109 models with a maximum weight exceeding 6000 lb have been approved following the grant of the exemption No. 6518 dated October 9, 1996. The Grant of Exemption No. 6648, Regulatory Docket No. 28353 was issued on June 25, 1997, for the A119 in response to Agusta letter of September 27, 1995, requesting exemption from 21.19(b)(1) of Title 14, Code of Federal Regulations (14 CFR) to allow for an amendment to the TC No. H7EU rather than applying for a new Type Certificate due to design change from 2 engine to one engine. Certification Basis (Cont’d). For the Model AW119 MKII: FAR 21.29 and FAR Part 27 as quoted below: FAR 27.1 a) Amdt. 37; FAR 27.2 Amdt. 28; FAR 27.2 b)2)i) Amdt. 37; FAR 27.21 Amdt. 21; FAR 27.25 Amdt. 36; FAR 27.27 Amdt. 2; FAR 27.29 Amdt. 14; FAR 27.33 Amdt. 14; FAR 27.45 Amdt. 21; FAR 27.51 Amdt. /; FAR 27.65 Amdt. 33; FAR 27.71 Amdt. 21; FAR 27.73 Amdt. /; FAR 27.75 Amdt. 14; FAR 27.79 Amdt. 21; FAR 27.141 Amdt. 21; FAR 27.143 Amdt. 21; FAR 27.151 Amdt. 21; FAR 27.161 Amdt. 21; FAR 27.171 Amdt. /; FAR 27.173 Amdt. 21; FAR 27.175 Amdt. 34; FAR 27.177 Amdt. 21; FAR 27.231 Amdt. /; FAR 27.241 Amdt. /; FAR 27.251 Amdt. /; FAR 27.301 Amdt. /; FAR 27.303 Amdt. /; FAR 27.305 Amdt. /; FAR 27.307 Amdt. 26; FAR 27.309 Amdt. /; FAR 27.321 Amdt. 11; FAR 27.337 Amdt. 26; FAR 27.339 Amdt. 11; FAR 27.341 Amdt. /; FAR 27.351 Amdt. 34; FAR 27.361 Amdt. 23; FAR 27.391 Amdt. 34; FAR 27.395 Amdt. 26; FAR 27.397 Amdt. 40; FAR 27.399 Amdt. /; FAR 27.401 Amdt. 27; FAR 27.403 Amdt. 27; FAR 27.411 Amdt. /; FAR 27.413 Amdt. 27; FAR 27.427 Amdt. 27; FAR 27.471 Amdt. /; FAR 27.473 Amdt. 2; FAR 27.501 Amdt. 26; FAR 27.505 Amdt. /; FAR 27.547 Amdt. 3; FAR 27.549 Amdt. 3; FAR 27.561 Amdt. /; FAR 27.571 Amdt. 26; FAR 27.601 Amdt. /; FAR 27.602 Amdt. 38; FAR 27.603 Amdt. 16; FAR 27.605 Amdt. 16; FAR 27.607 Amdt. 4; FAR 27.609 Amdt. /; FAR 27.610 Amdt. 37; FAR 27.611 Amdt. /; FAR 27.613 Amdt. 26; FAR 27.619 Amdt. /; FAR 27.621 Amdt. 34; FAR 27.623 Amdt. /; FAR 27.625 Amdt. /; FAR 27.629 Amdt. 26; FAR 27.653 Amdt. 2; FAR 27.659 Amdt. 2; FAR 27.661 Amdt. 2; FAR 27.663 Amdt. 26; Page 39 of 47 H7EU, Rev 32 FAR 27.671 Amdt. /; FAR 27.672 Amdt. 21; FAR 27.673 Amdt. 21; FAR 27.674 Amdt. 26; FAR 27.675 Amdt. 16; FAR 27.681 Amdt. /; FAR 27.683 Amdt. /; FAR 27.685 Amdt. 26; FAR 27.691 Amdt. /; FAR 27.695 Amdt. /; FAR 27.723 Amdt. /; FAR 27.725 Amdt. /; FAR 27.727 Amdt. 26; FAR 27.737 Amdt. /; FAR 27.771 Amdt. /; FAR 27.773 Amdt. /; FAR 27.775 Amdt. 27; FAR 27.777 Amdt. /; FAR 27.779 Amdt. 21; FAR 27.783 Amdt. 26; FAR 27.785 Amdt. /; FAR 27.787 Amdt. /; FAR 27.805 Amdt. 37; FAR 27.807 Amdt. 26; FAR 27.831 Amdt. /; FAR 27.853 Amdt. 17; FAR 27.855 Amdt. /; FAR 27.859 Amdt. 23; FAR 27.861 Amdt. 26; FAR 27.863 Amdt. 16; FAR 27.865 Amdt. 36; FAR 27.871 Amdt. /; FAR 27.901 Amdt. 23; FAR 27.903 Amdt. 23; FAR 27.907 Amdt. /; FAR 27.917 Amdt. 11; FAR 27.921 Amdt. /; FAR 27.923 Amdt. 29; FAR 27.927 Amdt. 23; FAR 27.931 Amdt. /; FAR 27.939 Amdt. 11; FAR 27.951 Amdt. 9; FAR 27.954 Amdt. 23; FAR 27.955 Amdt. 23; FAR 27.959 Amdt. /; FAR 27.961 Amdt. 23; FAR 27.963 Amdt. 23; FAR 27.965 Amdt. 12; FAR 27.967 Amdt. 30; FAR 27.969 Amdt. 23; FAR 27.971 Amdt. /; FAR 27.973 Amdt. /; FAR 27.975 Amdt. 30; FAR 27.977 Amdt. 11; FAR 27.991 Amdt. 23; FAR 27.993 Amdt. 2; FAR 27.995 Amdt. /; FAR 27.997 Amdt. 23; FAR 27.999 Amdt. 23; FAR 27.1011 Amdt. 23; FAR 27.1013 Amdt. 9; FAR 27.1017 Amdt. /; FAR 27.1019 Amdt. 23; FAR 27.1021 Amdt. 20; FAR 27.1027 Amdt. 23; FAR 27.1041 Amdt. 23; FAR 27.1043 Amdt. 14; FAR 27.1045 Amdt. 23; FAR 27.1091 Amdt. 23; FAR 27.1093 Amdt. 23; FAR 27.1121 Amdt. 12; FAR 27.1123 Amdt. 11; FAR 27.1141 Amdt. 33; FAR 27.1143 Amdt. 29; FAR 27.1145 Amdt. 12; FAR 27.1151 Amdt. 33; FAR 27.1163 Amdt. 23; FAR 27.1183 Amdt. 20; FAR 27.1185 Amdt. 11; FAR 27.1187 Amdt. /; FAR 27.1189 Amdt. 23; FAR 27.1191 Amdt. 2; FAR 27.1193 Amdt. 23; FAR 27.1194 Amdt. 2; FAR 27.1195 Amdt. 5; FAR 27.1301 Amdt. /; FAR 27.1303 Amdt. /; FAR 27.1305 Amdt. 29; FAR 27.1307 Amdt. /; FAR 27.1309 Amdt. 21; FAR 27.1321 Amdt. 13; FAR 27.1322 Amdt. 11; FAR 27.1323 Amdt. 13; FAR 27.1325 Amdt. 13; FAR 27.1327 Amdt. 13; FAR 27.1329 Amdt. 21; FAR 27.1337 Amdt. 23; FAR 27.1351 Amdt. 13; FAR 27.1353 Amdt. 14; FAR 27.1357 Amdt. 13; FAR 27.1361 Amdt. /; FAR 27.1365 Amdt. /; FAR 27.1367 Amdt. /; FAR 27.1381 Amdt. /; FAR 27.1383 Amdt. /; FAR 27.1385 Amdt. /; FAR 27.1387 Amdt. 7; FAR 27.1389 Amdt. /; FAR 27.1391 Amdt. /; FAR 27.1393 Amdt. /; FAR 27.1395 Amdt. /; FAR 27.1397 Amdt. 6; FAR 27.1399 Amdt. 2; FAR 27.1401 Amdt. 10; FAR 27.1411 Amdt. 11; FAR 27.1413 Amdt. 21; FAR 27.1435 Amdt. /; FAR 27.1461 Amdt. 2; FAR 27.1501 Amdt. 14; FAR 27.1503 Amdt. /; FAR 27.1505 Amdt. 21; FAR 27.1509 Amdt. /; FAR 27.1519 Amdt. 21; FAR 27.1521 Amdt. 29; FAR 27.1523 Amdt. /; FAR 27.1525 Amdt. 21; FAR 27.1527 Amdt. 14; FAR 27.1529 Amdt. 18; FAR 27.1541 Amdt. /; FAR 27.1543 Amdt. /; FAR 27.1545 Amdt. 16; FAR 27.1547 Amdt. 13; FAR 27.1549 Amdt. 29; FAR 27.1551 Amdt. /; FAR 27.1553 Amdt. /; FAR 27.1555 Amdt. 21; FAR 27.1557 Amdt. 11; FAR 27.1559 Amdt. 21; FAR 27.1561 Amdt. /; FAR 27.1565 Amdt. 2; FAR 27.1581 Amdt. 14; FAR 27.1583 Amdt. 16; FAR 27.1585 Amdt. 21; FAR 27.1587 Amdt. 21; FAR 27.1589 Amdt. /; FAR 27 Appendix A Amdt. 24. - Special Condition: HIRF Protection according to JAA Interim Policy, Paper No. INT/POL/27&29/1 [only for Electronic Engine Control System] - Special Condition: HIRF Protection according to JAA Interim Policy, Paper No. INT/POL/27&29/1 Issue 3 [only for “G1000H Installation Kit” P/N 109G4600F01- 101 and for G1000H NXi Installation Kit P/N 109G4600F01-201] - ELOS Memo AT04305RD-R-F-01 for G1000H NXi Installation Kit P/N 109G4600F01-201 Power Index Indicator - FAR 36, Appendix H, Amendment 36-28, January 2006 for the noise level determination. - For Pilot and Copilot Crashworthy Seats Installation Kit P/N 109G2510F04 and for Passenger Crashworthy Seats Installation Kit P/N 109G2520F45, installed, 14 CFR Page 40 of 47 H7EU, Rev 32 27.561 Amdt. 32; 14 CFR 27.562 Amdt. 25; 14 CFR 27.625 Amdt. 35; and 14 CFR 27.785 Amdt. 35 apply. See Note 21 for eligible serial helicopters for installation. The Certification basis applicable to the AW119 MKII model is identified in the Agusta document No. 109G0000N077. Date of Application for Type Certificate: February 18, 1971. Type Certificate No. H7EU issued June 1, 1975; amended April 2, 1976 to include Model A109A; amended December 4, 1981 to include Model A109AII; amended August 19, 1989 to include Model A109C; amended January 15, 1993 to include Model A109K2; amended August 26, 1996 to include Model A109E; amended April 28, 2000 to include Model A119.; amended July 20, 2006 to include Model A109S; amended October 22, 2007 to include Model AW119 MKII. amended October 14, 2010 to include Model AW109SP For IFR operations See NOTE 6. The Italian ENAC originally type certificated this under its type certificate number (A156). The FAA validated this product under U.S. Type Certificate Number (H7EU). Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the Italian ENAC. The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g. third party country) is FAR Sections 21.183(d) or 21.183(b). Import Requirements. To be considered eligible for operation in the United States, each aircraft manufactured under this type certificate must be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting foreign civil airworthiness authority which states (in the English language): The FAA can issue a U.S. airworthiness certificate based on a NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Italian ENAC or EASA on behalf of the European Community. The Export C of A should contain the following statement: “The aircraft covered by this certificate has been examined, tested, and found to comply with the EASA Type Certificate Number R.005 (formerly Italian ENAC TC Number A156) approved under the U.S. Type Certificate Number H7EU and to be in a condition for safe operation.” Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the rotorcraft for certification. In addition, the following items of equipment are required: (a) Approved Helicopter Flight Manual: 1. Model A109: A109 Helicopter Flight Manual dated May 21, 1975 or later revision. 2. Model A109A: A109A Helicopter Flight Manual dated May 16, 1979 or later revision. Page 41 of 47 H7EU, Rev 32 NOTE: for operations at 2450 Kg (5400 lbs) pages 1-2A, 1-2B and 1-12A are applicable. 3. Model A109A II: A109A II Helicopter Flight Manual dated June 2, 1981 or later revision. 4. Model A109C: A109C Helicopter Flight Manual dated October 2, 1989 or later revision. 5. Model A109K2: A109K2 Helicopter Flight Manual dated January 23, 1992 or later revision. 6. Model A109E: A109E Rotorcraft Flight Manual dated May 31, 1996 (PW206C) or later revision 7. Model A119: A119 Rotorcraft Flight Manual dated April 19, 2000 or later revision. 8. Model A109E: A109E Rotorcraft Flight Manual No. 109-08-053 and (TM 2K1) relevant Section 5 “Optional Equipment” No. 109-08-057, dated September 10, 2001 or later revision. 9. Model A109S A109S Rotorcraft Flight Manual No. 109G0040A013 and No. 109G0040A014 RFM Optional Equipment Supplements. Rotorcraft Flight Manual No. 109G0040A034 for A109S with Trekker Kit P/N 109G0000F01. 10. Model AW119 MKII AW119 MKII Rotorcraft Flight Manual No. 109G0040A017 or later revision AW119MKII equipped with “G1000H Installation Kit” P/N 109G4600F01-101and AW119MKII equipped with “G1000H NXi Installation Kit” P/N 109G4600F01-201 Rotorcraft Flight Manual No. 109G0040A033 or later revision 11. Model AW109SP AW109S Rotorcraft Flight Manual No. 109G0040A018 and No. 109G0040A019 RFM Optional Equipment Supplements (b) Low-rotor-rpm and engine-failure warning systems in accordance with Agusta drawing Nos. 109-0729-21 or 109-0729-31 and 109-0729-22 for A109A, A109AII and A119 Models; 109-0741-06 for Model A109C; 109-0741-27 and 109-0752-40 for Model A109K2; 109-0753-28 for Model A109E and A109S; 109-0900-66 for A119 Model equipped with Integrated Display System and AW119 MKII Model. (c) OAT indicator MS28028-1 On A109E, A109S, A119 equipped with Integrated Display System and AW119 MKII the OAT data are shown on the IDS system and the sensor is P/N E22307-2-4. Required and optional approved equipment are listed in the: A109 Equipment List Report No. 109-07-01; A109A Equipment List Report No. 109-07-03; A109AII Equipment List Report No. 109-07-06; A109C Equipment List Report No. 109-07-09; A109K2 Equipment List Report No. 109-07-14; A109E Equipment List Report No. 109-07-16; A119 Equipment List Report No. 109-07-19. A109S Equipment List Report No. 109G0840W017 Equipment List Report No. 109G0840W048 for A109S with Trekker Kit P/N 109G0000F01 AW119 MKII Equipment List Report No. 109G0840W030 Equipment List Report No. 109G0840W046 for “G1000H Installation Kit” and for “G1000H NXi Installation Kit” AW109SP Equipment List Report No. 109G0840W040 For IFR operations see NOTE 6. Placards. Placards listed in the EASA/ENAC-approved Helicopter Flight Manual must be displayed in the appropriate location. Page 42 of 47 H7EU, Rev 32 Service Information. Information essential for proper maintenance of the rotorcraft is presented in the following documentation which must be supplied with each rotorcraft at time of delivery: A109A/A109AII/A109C A109K2 A109E Airworthiness Limitations Section (Chapter 4) of the Maintenance Manual. A109S Airworthiness Limitations Section (Chapter 4) of the Doc n° 0B-A-AMPI-00-P Aircraft Maintenance Planning Information . A109A/A109AII/A109C A109K2 A109E inspection requirements and component overhaul schedule (chapter 5) of the Maintenance Manual. A109A/A109AII/A109C A109K2 A109E Maintenance Manual. A109S Airworthiness Limitations Section (Chapter 4) of the Doc n° 0B-A-AMPI-00-P Aircraft Maintenance Planning Information. A109S with Trekker Kit P/N 109G0000F01 Airworthiness Limitation Section (Chapter 4) of the Doc n° 0B-D-AMPI-00-P Aircraft Maintenance Planning Information. A119 ALS (Chapter 04) of the A119 / AW119 MKII Maintenance Planning Manual /of the A119 / AW119MKII 19-A-AMPI-00-P (see Note (A)). AW119 MKII ALS (Chapter 04A) of the A119 / AW119 MKII Maintenance Planning Manual / of the A119 / AW119MKII 19-A-AMPI-00-P (see Note (A)). NOTE: Mission profiles using more cycles than those quoted in the A119 and AW119 MKII ALS shall be communicated to the aircraft manufacturer for retirement lives recalculation and approval. A119 and AW119 MKII inspection requirements and component overhaul schedule (Chapter 05) of the A119 / AW119 MKII Maintenance Planning Manual / of the A119 / AW119 MKII 19-A-AMPI-00-P (see Note (A)). Note (A): Maintenance Manuals 19-A-AMPI-00-P replaced Maintenance Manuals A119/AW119MKII-MPM, which will no longer be kept updated. AW109SP Airworthiness Limitations Section (Chapter 4) of the Doc n° 0B-B-AMPI-00-P Aircraft Maintenance Planning Information and inspection requirements and component overhaul schedule (Chapter 5) of the Doc n° 0B-B-AMPI-00-P Aircraft Maintenance Planning Information “Agusta Service bulletins, structural repair manuals, vendor manuals, rotorcraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is European Aviation Safety Agency/ ENTE NAZIONALE AVIAZIONE CIVILE (EASA/ENAC) approved, are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only.” Mandatory Bulletins will be identified as such. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the Italian ENAC. Any such documents are accepted by the FAA and are considered FAA approved. • Service Bulletin, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. This applies only to the acceptance of type design data. NOTE 1. Current weight and balance report including list of equipment included in the certificated empty weight and loading instructions must be provided for each rotorcraft at the time of the original certification. The certificated empty weight and corresponding CG location must include undrainable oil and undrainable fuel. Page 43 of 47 H7EU, Rev 32 Undrainable engine oil is zero Kg. for all models except for the A109E where the undrainable oil is 2.09 Kg./4.61 lbs (0.567 U.S.gal/2.15 lt) at the sta. 4280 mm (168.5 in) and for the A119 and AW119 MKII where the undrainable oil is 1.6 Kg./3.52 lbs (0.433 U.S. gal/1.64 lt) at the sta. 4673 mm (183.9 in).and for theA109E where the undrainable oil is 1.8 /Kg/3.96 lbs (0.486 U.S gal/1.84 lt ) at sta 4280 mm (168.5 in). Unusable fuel is 7 Kg /15 lbs (2.4 U.S. gal./9 lt.) at sta. 3750 mm (148°) for Model A109A/AII/C, 9 Kg./20 lbs (3.2 U.S. gal./12 lit.) at sta. 3750 mm (148°) for Model A109K2, 8 Kg/17.6 lbs (2.66 U.S. gal./10 lt) at sta 3320 mm (131 in) for Model A109E, and 8 Kg/17.6 lbs (2.64 U.S. gal./10 lt) at sta 3320 mm (130.7 in) for Models A119 and AW119 MKII , and 9.6Kg/21.16 lbs (3.17 U.S gal /12 lt) at sta 3761 mm (148 in) for Model A109S and AW109SP. NOTE 2. All placards indicated in the Rotorcraft Flight Manual (RFM) must be installed in the appropriate location. NOTE 3. Life-limited components and approved retirement times of the Model A109A/A109AII/A109C/A109K2/ A109E/A119 /A109S/AW119 MKII and AW109SP are listed in the Chapter 04 “Airworthiness Limitations” of the applicable “Maintenance Manual” and must be replaced as prescribed therein. NOTE 4. For operation below 4ºC (40ºF) of the Model A109A/AII/C the use of anti-ice additive is authorized, but is not mandatory due to aircraft anti-ice fuel filter installation. Below 4ºC (40ºF) the AVGAS JET FUEL MIXTURE may be used as an alternative fuel. Refer to Allison Operation and Maintenance Manual for AVGAS mix, cold weather fuel and blending instructions. For A109E operation below 4ºC (40ºF) the use of anti-ice additive is authorized but not mandatory due to aircraft anti-ice fuel filter installation. For additive requirements and blending procedures refer to Pratt & Whitney or Turbomeca manuals. For A109S operation below 4ºC (40ºF) the use of anti-ice additive is authorized but not mandatory due to aircraft anti-ice fuel filter installation. For additive requirements and blending procedures refer to Pratt & Whitney PW207C engine /maintenance /installation manual For A119 and AW119 MKII operation below 4°C (40°F) the use of anti-ice additive is not mandatory, since the engine is equipped with a fuel heater. NOTE 5. For helicopters up to and including S/N 7114 not equipped with adjustable seat kit P/N 109-0700-49-1, moment arm of pilot and forward passenger seat is 1650 mm (65 in) from sta. 0. NOTE 6. a. Model A109A helicopters, S/N 7107, 7130 and subsequent, are eligible for day and night IFR operations, with one pilot or with two pilots, when "IFR" installation Agusta Kit No. 109-0810-22, Rev. E or later FAA-approved revision is incorporated and the helicopter is operated in accordance with Model A109A Flight Manual IFR Supplement No. 1 approved by RAI under date of July 16, 1978 and subsequent approved revisions. (NOTE: the above-noted kit and flight manual supplement comprise the Agusta version of FAA-approved STC No. CH2699SW). b. Model A109A II and A109C helicopters S/N 7256, and subsequent, are eligible for day and night IFR operations with one, or with two pilots when "IFR" installation Kit No. 109-0810-22, Rev. E or, later FAA approved revision, is incorporated and the helicopter is operated in accordance with Model A109 II and A109C Rotorcraft Flight Manuals. Page 44 of 47 H7EU, Rev 32 c. Model A109K2 helicopters S/N 10001 and subsequent, are eligible for day and night, single pilot IFR operation when IFR installation Agusta Kit No. 109-0810-22-135 and subsequent approved dash numbers are incorporated. Certification Basis: - Appendix B to Part 27 - Airworthiness criteria for helicopter instrument flight - Amdt. 27.19. - FAR Part 27 Paragraph 27.672 Amdt. 21; 27.1309 Amdt 21; 27.1329 Amdt 21; 27.1335 Amdt. 13. The helicopter shall be operated in accordance with the Model A109K2 Flight Manual IFR Supplement No. 2. d. Model A109E Helicopters S/N 11001 and subsequent, are eligible for day and night, single pilot IFR operation when IFR installation Agusta Kit P/N 109-0810-22-143 and subsequent approved dash numbers are incorporated. Certification Basis: - Appendix B to Part 27 - Airworthiness criteria for helicopter instrument flight - Amdt. 27.19. - FAR Part 27 Paragraph 27.672 Amdt. 21; 27.1309 Amdt 21; 27.1329 Amdt 21; 27.1335 Amdt. 13. The helicopter shall be operated in accordance with the Model A109E Flight Manual. e. Model A109S Helicopters S/N 22001 and subsequent, are eligible for day and night, single pilot IFR operation. The IFR is part of the Basic Certification. f. Model AW109SP Helicopters S/N 22201, 22203, and 22214 and subsequent, are eligible for day and night, single pilot IFR operation. The IFR is part of the Basic Certification NOTE 7. Model A109A helicopters are eligible for operations at maximum weight of 2600 kg (5732 lb.) when Agusta Technical Bulletin No.109-20 and subsequent approved revisions are incorporated. For Model A109A helicopters not incorporating the Agusta Technical Bulletin No. 109-20, the following limitations are to be applied. - Airspeed limits Never exceed speed (VNE) 168 kts IAS For reduction of VNE with altitude and OAT, see page 1-2A of the FAA-approved Rotorcraft Flight Manual. - CG Range (Gear Down) Longitudinal Limits -- Refer to diagram on page 5 (Model A109A) for weight up to 2450 kg. (5400 lb.) Lateral Limits -- Refer to diagram on page 6 (Model A109A) for weight up to 2450 kg. (5400 lb.) - Maximum Weight 2450 kg (5400 lb.) See Page 1-2B of the FAA-approved Rotorcraft Flight Manual. - Maximum Operating Altitude 4560m (15000 ft) See Page 1-2B of the FAA-approved Rotorcraft Flight Manual. NOTE 8. For Models A109AII, A109C, and A109K2, the auxiliary fuel tank installation P/N 109-0810-56 adds a total fuel capacity of 40.8 U.S. Gal. (153 lit.) at sta. 4708 mm (185.3 in.) of which 40 U.S. Gal. (150 lit.) is usable. For Model A109E, the fuel tank installation P/N 109-0811-49 adds a total of fuel capacity of 70 U.S. gal. (265 lit.) all usable. For Model A109S the fuel tank installation P/N 109-0813-32 adds a total of fuel capacity of 060.76 U.S. Gal. (230 lit) all usable. For Model A119 and AW119 MKII the fuel tank installation P/N 109-0811-49 adds a total of fuel capacity of 70 US Gal. (265 lit) all usable. For Model AW109SP the fuel tank installation P/N 109-0813-32 adds a total of fuel capacity of 60.76 U.S. Gal. (230 lit) all usable NOTE 9. The Models A109/A109A/A109AII/A109C/A109K2/A109E/A119/A109S/AW119 MKII /AW109SP are identified by the general assembly drawing as follows: 109-9000-01-5 for A109 109-9000-01-11/15/19/23/27 for A109A 109-9000-01-31 for A109AII 109-9000-01-135 for A109C 109-9000-01-139 for A109K2 109-9000-01-149 for A109E 119-9000-01-107 for A119 109-9000-09-101 for A109S 119-9000-01-111 for AW119 MKII 109-9000-09-105 for AW109SP Page 45 of 47 H7EU, Rev 32 NOTE 10. The model A109K2 is eligible for operations on clear airfield and helipad with the critical engine failure concept when the installation P/N 109-0822-47 (all the approved dashes) is incorporated and the helicopter is operated in accordance with the Model A109K2 Flight Manual Supplement No. 3 "Take-off and landing procedures and performance data on clear airfield and helipad with critical engine failure". Certification Basis: That applicable to the A109K2 plus JAR 29.45(a), (b)(2) Amdt. Base; JAR 29.49(a) Amdt. Base; JAR 29.51 Amdt. Base; JAR 29.53 Amdt. Base; JAR 29.55 Amdt. Base; JAR 29.59 Amdt. Base; JAR 29.60 Amdt. Base; JAR 29.61 Amdt. Base; JAR 29.62 Amdt. Base; JAR 29.64 Amdt. Base; JAR 29.65 (a) Amdt. Base; JAR 29.67 (a) Amdt. Base; JAR 29.75 Amdt. Base; JAR 29.77 Amdt. Base; JAR 29.79 Amdt. Base; JAR 29.81 Amdt. Base; JAR 29.85 Amdt. Base; JAR 29.87 (a) Amdt. Base; FAR 29.861(a) Amdt. 26; FAR 29.901(c) Amdt. 25 for engines installations only; FAR 29.901 (c) Amdt. 25. For engines installation only; FAR 29.903(b), (c), (e) Amdt. 31; FAR 29.908(a) Amdt. 25; FAR 29.923 Amdt. 23; FAR 27.927 (a), (b) Amdt. 12; FAR 29.927 (c)(1) Amdt. 26; FAR 29.953 (a) Amdt. Base; JAR 29.1027(a) Amdt. Base; JAR 29.1045 (a)(1), (b), (c), (d), (f) Amdt. Base; JAR 29.1047 (a) Amdt. Base; JAR 29.1181 (a) Amdt. Base; JAR 29.1187 (e) Amdt. Base; JAR 29.1189 (c) Amdt. Base; JAR 29.1191 (a)(1) Amdt. Base; JAR 29.1193 (e) Amdt. Base; JAR 29.1305 (a)(6), (b) Amdt. Base; JAR 29.1309 (b)(2)(i), (d) Amdt. Base; JAR 29.1323 (e)(1) Amdt. Base; JAR 29.1331 (b) Amdt. Base; JAR 29.1587 (a) Amdt. Base. The JAR requirements listed above meet or exceed the FAR Part 27 and FAR Part 29 CAT A. requirements. NOTE 11. The Model A109E is eligible for operations on clear airfield and helipad with the “Equivalent Category A” when the installation P/N 109-0811-39 (all the approved dashes) is incorporated and the helicopter is operated in accordance with the Model A109E Flight Manual Supplement No. 12 Equivalent Category “A” operations. In addition to the paragraphs of the Certification Basis, the A109E must comply also with the following paragraphs: JAR 29.45(a),(b)(2) Amendment base; JAR 29.49(a) Amendment base; JAR 29.51 Amendment base; JAR 29.53 Amendment base; JAR 29.55 Amendment base, JAR 29.59 Amendment base; JAR 29.60 Amendment base; JAR 29.61 Amendment base; JAR 29.62 Amendment base; JAR 29.64 Amendment base; JAR 29.65 (a) Amendment base; JAR 29.67 (a) Amendment base; JAR 29.75 Amendment base; JAR 29.77 Amendment base; JAR 29.79 Amendment base; JAR 29.81 Amendment base; JAR 29.85 Amendment base; JAR 29.87 (a) Amendment base; (JAR 29.571 Amendment base Fatigue evaluation of structure.) AC Material only: AC 29-2A Item 230 Paragraph 10; JAR 29.861 (a) Amendment base; JAR 29.901 (c) Amendment base; JAR 29.903 (b), (c), (e) Amendment base; JAR 29.908 (a) Amendment base; JAR 29.927 (c)(1), JAR 29.953(a) Amendment base; JAR 29.1027(a) Amendment base; JAR 29.1045 (a)(1), (b), (c), (d), (f) Amendment base; JAR 29.1047 (a) Amendment base; JAR 29.1181(a)(1) Amendment base; JAR 29.1193 (e) Amendment base; JAR 29.1195(a), (d) Amendment base; JAR 29.1305 (a)(6),(b) Amendment base; JAR 29.1309 (b)(2)(i), (d) Amendment base; JAR 29.1323 (c)(1) Amendment base; JAR 29.1331 (b) Amendment base; JAR 29.1351(d)(2) Amendment base; JAR 29.1587 (a) Amendment base. The JAR requirements listed above meets the FAR Part 27 and FAR Part 29 CAT A. requirements. NOTE 12. For the models A109K2 and A109E that has been certified with ditching provisions in accordance with RFM supplements No. 22 & 21 respectively the certification basis has been updated adding with the following paragraphs: FAR 27.563 Amendment 26, FAR 27.801 Amendment 11, FAR 27.807 Amendment 26, FAR 27.1411 Amendment 11, FAR 27.1415 Amendment 11. NOTE 13. The model A109E, A109S and AW109SP rotorcraft employ electronic engine controls, commonly named Full Authority Digital Engine Controls (FADEC), and is recognized to be more susceptible to Electromagnetic Interference (EMI) than rotorcraft that have only manual (non-electronic) controls. EMI may be the result of radiated or conducted interference. For this reason modifications that add or change systems that have the potential for EMI, must be either qualified to a standard acceptable to the FAA or tested at the time of installation for interference to the FADEC. This type of testing must employ the particular FADEC’s diagnostic techniques and external diagnostic techniques. The test procedure must be FAA approved. NOTE 14. The model A109E may be equipped with either PW206C or TM 2K1 turboshaft engines. Changes to the approved TC holder Type Design, that may have an effect on engine installation or operation, must be limited in applicability to the engine installation for which they have been tested and approved. NOTE 15. Model A109 helicopters may be converted to Model A109A helicopters in accordance with EASA/ENAC- approved Service Instructions No. A109-1. Page 46 of 47 H7EU, Rev 32 NOTE 16. Cabin Interior and Seating Configurations must be approved. NOTE 17. Any changes to the type design of this helicopter by means of an amended type certificate (TC), supplemental type certificate (STC), or amended STC, requiring instructions for continued airworthiness (ICA's) must be submitted thru the project aircraft certification office (ACO) for review and acceptance by the Fort Worth -Aircraft Evaluation Group (FTW-AEG) Flight Standards District Office (FSDO) prior to the aircraft delivery, or upon issuance of the first standard airworthiness certificate for the affected aircraft, whichever occurs later as prescribed by Title 14 CFR 21.50. Type design changes by means of a field approval that require ICA's must have those ICA's reviewed by the field approving FSDO. NOTE 18. Effective August 24, 2006, the model A119, from serial number 14517 up to 14700, and the model AW119MKII, from serial number S/N 14701 to S/N 15499 (excluding S/N 15015, S/N 15016, S/N 15019 and S/N 15023) and from S/N 15800 to S/N 15999 are approved for production at Agusta Aerospace Corporation's (AAC), Philadelphia facility under Production Certificate PC 120NE. This PC is based on a Decision Paper / Licensing Agreement approved on February 24, 2005. All technical data previously developed by Agusta S.p A. in support of this model and approved by ENAC, and further approved by the FAA under the requirements of FAR 21.29 and the BASA between the US and Italy, are still in effect and any revisions to that data will still need to be FAA approved as previously agreed upon prior to the issuance of this PC. All export tags will need to document that this model and serial number were manufactured in Agusta AAC’s Philadelphia facility. Effective 01 June 2011, the Agusta Aerospace Corporation name was changed to AgustaWestland Philadelphia Corporation. Effective 02 December 2011, PC120NE was changed to reflect the Agusta Aerospace Corporation name change to AgustaWestland Philadelphia Corporation. Effective 09 June 2026, AgustaWestland Philadelphia Corporation name was changed to Leonardo Helicopters United States Corporation (LHUSC). Effective March 25, 2022, the model AW119MKII, from serial number S/N 15500 to S/N 15799 (and including S/N 15015, S/N 15016, S/N 15019 and S/N 15023), are approved for production at Leonardo S.p.A. Helicopters, Vergiate facility under Production Organization Approval Certificate IT.21G.0007. NOTE 19. The Model A109S is eligible for Category A operations when the installation P/N 109-0823-98 (all the approved dash numbers) is incorporated and the helicopter is operated in accordance with the Model A109S Rotorcraft Flight Manual No. 109G0040A013 and No. 109G0040A014 RFM Optional Equipment Supplements No. 7 Category A Operations. In addition to the paragraphs of the Certification Basis, the A109S complies with JAR 27 Appendix C. The JAR requirements listed in the JAR 27 Appendix C meets the Appendix C to FAR PART 27 Criteria for Category A. The Model A109S with Trekker Kit P/N 109G0000F01 is eligible for Category A operations when the Engine Fire Extinguisher Kit P/N 109-0811-39-109 is installed. Refer to RFM 109G0040A034 Supplement No. 4 Category A Operations. In addition to the paragraphs of the Certification Basis, the A109S with Trekker Kit P/N 109G0000F01 complies with CS 27 Amdt.3 Appendix C. The CS requirements listed in the CS 27 Appendix C meets the Appendix C to FAR PART 27 Criteria for Category A. Refer to Leonardo document No. 109G0274A001. NOTE 20. The Model AW109SP is eligible for Category A operations when operated in accordance with the Model AW109SP Rotorcraft Flight Manual No. 109G0040A018 and No. 109G0040A019 RFM Optional Equipment Supplements No. 4 Category A Operations. In addition to the paragraphs of the Certification Basis, the AW109SP complies with CS 27 Appendix C. The CS requirements listed in the CS 27 Appendix C meets the Appendix C to FAR PART 27 Criteria for Category A. NOTE 21. For models AW119MKII, Pilot and Copilot Crashworthy Seats Installation Kit P/N 109G2510F04 and Passenger Crashworthy Seats Installation Kit P/N 109G2520F45 are eligible for installation on helicopters S/N 15001 and subs. Page 47 of 47 H7EU, Rev 32 NOTE 22. For model A109S with Trekker Kit P/N 109G0000F01: PEDs sensitive equipment, which are under the responsibility of the TC Holder and are declared as NON-PED tolerant, or have PED tolerance limitations are reported in the document 109G9850A002 “A109S Trekker - PED Compatibility Reference Handbook". NOTE 23 For model AW109SP: PEDs sensitive equipment, which are under the responsibility of the TC Holder and are declared as NON-PED tolerant, or have PED tolerance limitations are reported in the document 109G9850A001 “AW109SP - PED Compatibility Reference Handbook”. ….. END ….. ``` ## ADs (143, first 50, in force first) - [AD 2026-17-05](https://openairdocs.org/ad/2026-17-05): Cabin Equipment/Furnishings · Airbus Helicopters H160-B, EC225LP, AS 365 N3 and 18 more. Effective Oct 2, 2026 - [AD 2026-17-07](https://openairdocs.org/ad/2026-17-07): Main rotor mast/swashplate · Leonardo A109A, A109A II, A109C and 6 more. Effective Oct 2, 2026 - [AD 2026-09-09](https://openairdocs.org/ad/2026-09-09): Fuselage structure · Leonardo A109E and A109S. Effective Jun 17, 2026 - [AD 2025-25-13](https://openairdocs.org/ad/2025-25-13): Powerplant System · Leonardo AW119 MKII and A119. Effective Jan 13, 2026 - [AD 2025-18-01](https://openairdocs.org/ad/2025-18-01): Main Rotor Head · Leonardo A109E, A109S, AW109SP and 2 more. Effective Sep 25, 2025 - [AD 2025-17-10](https://openairdocs.org/ad/2025-17-10): Main Rotor Control · Leonardo A109A, A109A II, A109C and 3 more. Effective Sep 9, 2025 - [AD 2025-09-06](https://openairdocs.org/ad/2025-09-06): Battery/charger system · Leonardo A119 and AW119 MKII. Effective Jun 16, 2025 - [AD 2025-09-10](https://openairdocs.org/ad/2025-09-10): Extinguishing System · Leonardo A109E, A109S and AW109SP. Effective Jun 16, 2025 - [AD 2025-07-07](https://openairdocs.org/ad/2025-07-07): Main Rotor Blades · Leonardo A109C, A109E, A109S and 1 more. Effective May 23, 2025 - [AD 2025-07-01](https://openairdocs.org/ad/2025-07-01): Air Data Computer · Synthetic Vision Electronic Flight Information System (Arrow STC SR09595RC or ST01523WI). Effective May 15, 2025 - [AD 2025-03-03](https://openairdocs.org/ad/2025-03-03): Cabin Equipment/Furnishings · Leonardo A109E, A109K2, A109S and 4 more. Effective Feb 19, 2025 - [AD 2024-18-01](https://openairdocs.org/ad/2024-18-01): Rotorcraft Flight Control · Leonardo A119 and AW119 MKII. Effective Nov 12, 2024 - [AD 2024-15-11](https://openairdocs.org/ad/2024-15-11): Tail Rotor System · Leonardo A109C, A109E, A109K2 and 2 more. Effective Oct 21, 2024 - [AD 2023-25-08](https://openairdocs.org/ad/2023-25-08): Main Rotor System · Leonardo A109E, A109S, AW109SP and 2 more. Effective Feb 2, 2024 - [AD 2023-17-07](https://openairdocs.org/ad/2023-17-07): Starter-Generator · Leonardo A119 and AW119 MKII. Effective Nov 1, 2023 - [AD 2023-11-07](https://openairdocs.org/ad/2023-11-07): Ground Proximity System · Airbus Helicopters 47, 206, 210 and 237 more. Effective Jun 22, 2023 - [AD 2023-01-02](https://openairdocs.org/ad/2023-01-02): Emergency Equipment · Apical Industries, Inc. Emergency Float Kit (STC SR01812LA). Effective Feb 17, 2023 - [AD 2022-11-06](https://openairdocs.org/ad/2022-11-06): rotorcraft Flight Control · Leonardo A109S. Effective Jul 6, 2022 - [AD 2022-06-19](https://openairdocs.org/ad/2022-06-19): Emergency Equipment · Leonardo AW109SP. Effective May 11, 2022 - [AD 2022-07-11](https://openairdocs.org/ad/2022-07-11): Tail Rotor System · Leonardo A109C, A109K2, A109E and 2 more. Effective May 5, 2022 - [AD 2022-05-10](https://openairdocs.org/ad/2022-05-10): Cabin Equipment/Furnishings · Airbus Helicopters AS332L, AS332L1, AS332L2 and 57 more. Effective Apr 20, 2022 - [AD 2021-26-24](https://openairdocs.org/ad/2021-26-24): Main Rotor Blades · Leonardo A109A and A109A II. Effective Feb 22, 2022 - [AD 2021-23-10](https://openairdocs.org/ad/2021-23-10): Hydraulic Pump (Elect/Eng), Main · Leonardo AW109SP. Effective Feb 4, 2022 - [AD 2021-25-01](https://openairdocs.org/ad/2021-25-01): Electrical Power System Wiring · Leonardo A109S and AW109SP. Effective Jan 24, 2022 - [AD 2021-24-11](https://openairdocs.org/ad/2021-24-11): Main Landing Gear Strut/Axle/Truck · Leonardo A109E, A109S and AW109SP. Effective Jan 14, 2022 - [AD 2021-22-10](https://openairdocs.org/ad/2021-22-10): Tail Rotor Gearbox · Leonardo A109E. Effective Dec 27, 2021 - [AD 2021-21-03](https://openairdocs.org/ad/2021-21-03): Rotorcraft Flight Control, Rotorcraft Servo System · Leonardo A109A, A109A II, A109C and 6 more. Effective Dec 10, 2021 - [AD 2021-20-18](https://openairdocs.org/ad/2021-20-18): Passenger compartment doors · Leonardo AW119 MKII. Effective Nov 3, 2021 - [AD 2021-16-06](https://openairdocs.org/ad/2021-16-06): Tail Rotor Drive Shaft · Leonardo A119 and AW119 MKII. Effective Sep 27, 2021 - [AD 2021-16-13](https://openairdocs.org/ad/2021-16-13): Stabilizer Control System · Leonardo A109S and AW109SP. Effective Sep 22, 2021 - [AD 2021-17-10](https://openairdocs.org/ad/2021-17-10): Main Rotor Brake · Leonardo A109A, A109A II, A109C and 4 more. Effective Sep 7, 2021 - [AD 2021-14-14](https://openairdocs.org/ad/2021-14-14): Instrument System Wiring · Leonardo AW119 MKII. Effective Jul 26, 2021 - [AD 2021-10-24](https://openairdocs.org/ad/2021-10-24): Tail Rotor Control System · Leonardo A109A and A109A II. Effective Jun 18, 2021 - [AD 2021-05-04](https://openairdocs.org/ad/2021-05-04): Fuselage Wiring, Baggage Fairings Modification · Leonardo A109S and AW109SP. Effective Apr 16, 2021 - [AD 2021-07-05](https://openairdocs.org/ad/2021-07-05): Main Rotor Blades · Leonardo A109C, A109E and A109K2. Effective Apr 8, 2021 - [AD 2021-03-15](https://openairdocs.org/ad/2021-03-15): Tail Rotor System · Leonardo A119 and AW119 MKII. Effective Apr 1, 2021 - [AD 2020-26-10](https://openairdocs.org/ad/2020-26-10): Placards and markings · Leonardo A119 and AW119 MKII. Effective Feb 1, 2021 - [AD 2020-21-21](https://openairdocs.org/ad/2020-21-21): Main Rotor Head · Leonardo A109E, A109S, A119 and 2 more. Effective Nov 24, 2020 - [AD 2020-20-02](https://openairdocs.org/ad/2020-20-02): Extinguishing System · Leonardo A109E, A109S and AW109SP. Effective Nov 3, 2020 - [AD 2020-15-16](https://openairdocs.org/ad/2020-15-16): Tail Rotor Drive System · Leonardo A109E, A109K2, A109S and 3 more. Effective Aug 27, 2020 - [AD 2019-09-04](https://openairdocs.org/ad/2019-09-04): Cabin Equipment/Furnishings · Leonardo AW109SP. Effective Jul 3, 2019 - [AD 2018-16-01](https://openairdocs.org/ad/2018-16-01): Equipment · B/E Aerospace Fischer A109, AW169, Attendant seats NG and 1 more. Effective Aug 31, 2018 - [AD 2018-16-08](https://openairdocs.org/ad/2018-16-08): Rotorcraft Cooling Fan System · Leonardo A109E, A109S and AW109SP. Effective Aug 20, 2018 - [AD 2018-06-51](https://openairdocs.org/ad/2018-06-51): Main Rotor Mast/Swashplate · Agusta A109A, A109A II, A109C and 6 more. Effective Jun 7, 2018 - [AD 2018-07-02](https://openairdocs.org/ad/2018-07-02): Main Rotor Blades · Agusta A109E, A109S, A119 and 2 more. Effective Apr 13, 2018 - [AD 2017-25-17](https://openairdocs.org/ad/2017-25-17): Elevator Structure · Agusta A109S and AW109SP. Effective Jan 4, 2018 - [AD 2017-18-13](https://openairdocs.org/ad/2017-18-13): Main Rotor Blade · Agusta A109A and A109A II. Effective Sep 25, 2017 - [AD 2017-16-02](https://openairdocs.org/ad/2017-16-02): Cabin Equipment/Furnishings · Agusta A109S. Effective Sep 5, 2017 - [AD 2016-18-18](https://openairdocs.org/ad/2016-18-18): Tail Rotor Drive Shaft · Agusta A109A, A109A II, A109C and 4 more. Effective Oct 20, 2016 - [AD 2015-05-51](https://openairdocs.org/ad/2015-05-51): Main Rotor Blades · Agusta A109A and A109A II. Effective Jul 1, 2015 All 143: https://openairdocs.org/tcds/H7EU/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Agustawestland Philadelphia AW119MKII](https://openairdocs.org/model/agustawestland-philadelphia-aw119mkii): 180 aircraft (registry code 0260401) - [Agusta A109E](https://openairdocs.org/model/agusta-a109e): 55 aircraft (registry code 0260101) - [Leonardo AW109SP](https://openairdocs.org/model/leonardo-aw109sp): 19 aircraft (registry code 33601QA) - [Agusta A109S](https://openairdocs.org/model/agusta-a109s): 18 aircraft (registry code 0260103) - [Agusta A109A II](https://openairdocs.org/model/agusta-a109a-ii): 17 aircraft (registry code 0260120) - [Agusta A109C](https://openairdocs.org/model/agusta-a109c): 12 aircraft (registry code 0260118) - [Agusta A119](https://openairdocs.org/model/agusta-a119): 12 aircraft (registry code 0260102) - [Agusta Aerospace AW119 MKII](https://openairdocs.org/model/agusta-aerospace-aw119-mkii): 6 aircraft (registry code 0260105) - [Agustawestland AW109SP](https://openairdocs.org/model/agustawestland-aw109sp): 6 aircraft (registry code 0260116) - [Agusta A109A](https://openairdocs.org/model/agusta-a109a): 5 aircraft (registry code 0260112) - [Agusta AW109SP](https://openairdocs.org/model/agusta-aw109sp): 4 aircraft (registry code 0260113) - [Agusta AGUSTA A109](https://openairdocs.org/model/agusta-agusta-a109): 3 aircraft (registry code 0260109) - [Agustawestland A109S](https://openairdocs.org/model/agustawestland-a109s): 3 aircraft (registry code 0260117) - [Agusta S P A A109K2](https://openairdocs.org/model/agusta-s-p-a-a109k2): 2 aircraft (registry code 0260502) - [Agustawestland A109SP](https://openairdocs.org/model/agustawestland-a109sp): 2 aircraft (registry code 0260114) - [Leonardo S P A A109S](https://openairdocs.org/model/leonardo-s-p-a-a109s): 2 aircraft (registry code 33601QD) - [Agusta AW119MKII](https://openairdocs.org/model/agusta-aw119mkii): 1 aircraft (registry code 0260130) - [Agusta S P A Construzioni Aero A109E](https://openairdocs.org/model/agusta-s-p-a-construzioni-aero-a109e): 1 aircraft (registry code 0260659) - [Agusta-Bell A 109A](https://openairdocs.org/model/agusta-bell-a-109a): 1 aircraft (registry code 0260300) - [Agustawestland Philadelphia AW109SP](https://openairdocs.org/model/agustawestland-philadelphia-aw109sp): 1 aircraft (registry code 0260119) - [Agusta 109A](https://openairdocs.org/model/agusta-109a): 0 aircraft (registry code 0260199) - [Agusta A109SP](https://openairdocs.org/model/agusta-a109sp): 0 aircraft (registry code 0260107) - [Agusta Aerospace A119](https://openairdocs.org/model/agusta-aerospace-a119): 0 aircraft (registry code 0260104) - [Agusta Westland AGUSTA 109A](https://openairdocs.org/model/agusta-westland-agusta-109a): 0 aircraft (registry code 0260189) - [Agustawestland A109E](https://openairdocs.org/model/agustawestland-a109e): 0 aircraft (registry code 0260115) - [Agustawestland Philadelphia AW119 MK](https://openairdocs.org/model/agustawestland-philadelphia-aw119-mk): 0 aircraft (registry code 0260404) - [Leonardo A109E](https://openairdocs.org/model/leonardo-a109e): 0 aircraft (registry code 33601QB) ## STCs approved under this data sheet (185, first 50) - [STC SR12441MC](https://openairdocs.org/stc/SR12441MC): Installation of exterior NVIS compatible formation lights. Leonardo Helicopters US Corporation - [STC SR01943NY](https://openairdocs.org/stc/SR01943NY): Installation of an Enhanced Ground Proximity Warning System (EGPWS).. Leonardo Helicopters US Corporation - [STC SR02150NY](https://openairdocs.org/stc/SR02150NY): Installation of an Enhanced Vision System (EVS-1000).. Leonardo Helicopters US Corporation - [STC SR02752NY](https://openairdocs.org/stc/SR02752NY): Installation of a Garmin GNS430W System. Leonardo Helicopters US Corporation - [STC SR03138NY](https://openairdocs.org/stc/SR03138NY): Revised the low limit of the normal operating envelope of the rotorcraft for cold weather operation to allow operation at minimum ambient air temperature of -35 C (-31 F). Leonardo Helicopters US Corporation - [STC SR02520AK](https://openairdocs.org/stc/SR02520AK): Installation of Avionics and auxiliary generator (Configurations A1, A2, A3, E1, D1, X) for certification of Single Pilot Instrument Flight Rules (SPIFR) Operations. Leonardo Helicopters US Corporation - [STC SR03005NY](https://openairdocs.org/stc/SR03005NY): Installation of Night Vision Goggle (NVG) Compatible Lighting System for NVG Operation. Leonardo Helicopters US Corporation - [STC SR03280NY](https://openairdocs.org/stc/SR03280NY): Installation of a Garmin G1000H PFD/MFD Display System. Leonardo Helicopters US Corporation - [STC SR04231NY](https://openairdocs.org/stc/SR04231NY): Installation of the Utility Installations, ID No. AWPC-ENG-17-037-A1 through AWPC-ENG-17-037-A27. Leonardo Helicopters US Corporation - [STC SR04601NY](https://openairdocs.org/stc/SR04601NY): Installation of a crash resistant fuel system (CRFS) and optional closed circuit refueling receiver (CCRR). Leonardo Helicopters US Corporation - [STC SR04464NY](https://openairdocs.org/stc/SR04464NY): Installation of the iPad Mount. Avio Design Group Inc. - [STC SR04842NY](https://openairdocs.org/stc/SR04842NY): Installation of RMCI Inc. Expandable Rotorcraft Diagnostic System (XRDS). Sterling Helicopter - [STC SR00824DE](https://openairdocs.org/stc/SR00824DE): Installation of an Emergency Medical Services Interior and alternate cabin seating interior configurations. AMS Heli Design - [STC SR03201CH](https://openairdocs.org/stc/SR03201CH): Installation of Heli-Preheat System, P/N 2862-1 for 115 volt application. Hartzell Propeller LLC - [STC SR04195CH](https://openairdocs.org/stc/SR04195CH): Installation of Heli-Preheat Kit, P/N TA3134-1 for 115-volt application. Hartzell Propeller LLC - [STC SR00182IB](https://openairdocs.org/stc/SR00182IB): Installation of the Avidyne Integrated Flight Display (IFD) Navigator(s). Horizon Design Services Ltd. - [STC SR04838NY](https://openairdocs.org/stc/SR04838NY): Installation of optional recording system under Configuration A1, which consists of L3Harris Modular Airborne Data recording/Acquisition Systems (MADRAS) Cockpit Voice and Data Recorder (CVDR) system. AgustaWestland Philadelphia Corporation (AWPC) - [STC SR02454LA](https://openairdocs.org/stc/SR02454LA): Installation of Essex Cryogenics LOX System. M7 Aerospace LLC - [STC SH3319NM](https://openairdocs.org/stc/SH3319NM): Installation of Precise Flight Pulselite Control Unit in the Landing /Taxi Recognition Visual Control Light system,. Precise Flight Inc - [STC SR04557AT](https://openairdocs.org/stc/SR04557AT): Cabin and crew floor protector installations. Helifab East LLC - [STC SR01392LA](https://openairdocs.org/stc/SR01392LA): Installation of Apical Industries, Inc. Emergency Float Kits. Dart Aerospace ULC - [STC SR00084IB](https://openairdocs.org/stc/SR00084IB): Installation of Alternative Inflation System for Emergency Flotation System. SAAB AKTIEBOLAG - [STC SR01456LA](https://openairdocs.org/stc/SR01456LA): Installation of Concorde RG407 Batteries. Rotorcraft Support Inc - [STC SR00463DE](https://openairdocs.org/stc/SR00463DE): Installation of Cabin Air Conditioning System.. Air Comm Corporation - [STC SR04007AT](https://openairdocs.org/stc/SR04007AT): Replace original equipment Nickel-Cadmium (NiCd) or Concorde Lead-Acid main battery with higher capacity Concorde Lead-Acid, main battery on Agusta A119 and AW119 MKII rotorcraft and associated hardware. Concorde Battery Corporation - [STC SR04601 NY](https://openairdocs.org/stc/SR04601%20NY): Installation of a crash resistant fuel system (CRFS). AgustaWestland Philadelphia Corporation - [STC SR02704SE](https://openairdocs.org/stc/SR02704SE): Installation and maintenance of the Sunspot 36 and 46 series lights. AeroLED's Holdings LLC - [STC SR01970NY-D](https://openairdocs.org/stc/SR01970NY-D): Installation of a Honeywell Chadwick Model 15175 VXP System.. Diagnostic Solution International LLC - [STC SR09917AC](https://openairdocs.org/stc/SR09917AC): Installation of an Advanced Life Support System (ALSS) airborne EMS air ambulance interior. AMS Heli Design LLC - [STC SR01052DE](https://openairdocs.org/stc/SR01052DE): Installation of Non-Aviation Band FM Radio Systems. Cert Works LLC - [STC SR01476SE](https://openairdocs.org/stc/SR01476SE): Installation of a Supplemental Lighting System.. Aviation Specialties Unlimited Inc. - [STC SR00949SE](https://openairdocs.org/stc/SR00949SE): Fabrication of Dart D119-647-011 Bearpaws. Dart Aerospace USA Inc. - [STC SH301NM](https://openairdocs.org/stc/SH301NM): Installation of a Sperry AA-300 radio altimeter system.. Honeywell International Inc - [STC SH300NM](https://openairdocs.org/stc/SH300NM): Installation of a Sperry Primus300SL or 400SL weather radar system and new nose radome.. Honeywell International Inc - [STC SR04453CH](https://openairdocs.org/stc/SR04453CH): Installation of Appareo Systems LLC Stratus ES & Stratus ESG ADS-B transponder. Appareo Systems LLC - [STC SR02124SE](https://openairdocs.org/stc/SR02124SE): Installation functionality. of Data Garmin Required: transponders: (1) Garmin GTX Master 345/345R Drawing with List ADS-B (MDL), Out and In 005-00734-A4, functionality;. Garmin International Inc - [STC SR04441NY](https://openairdocs.org/stc/SR04441NY): Installation of Night Vision Goggle (NVG) Compatible Lighting System, Configuration A. AgustaWestland Philadelphia Corporation - [STC SR04390CH](https://openairdocs.org/stc/SR04390CH): Installation of an Electronic Flight Instrument System (EFIS) in accordance with StandardAero Master Data List 1036284, Revision (B), dated June 5, 2019 or later FAA approved revision.. StandardAero Business Aviation Services LLC - [STC SR00359BO](https://openairdocs.org/stc/SR00359BO): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SR01525NY](https://openairdocs.org/stc/SR01525NY): Installation of an Emergency Medical System (EMS).. LifePort LLC - [STC SR01816LA](https://openairdocs.org/stc/SR01816LA): Installation of a Medical Stretcher.. LifePort LLC - [STC SR01865LA](https://openairdocs.org/stc/SR01865LA): Installation of an Emergency Medical Rescue Stretcher.. LifePort LLC - [STC SR00814DE](https://openairdocs.org/stc/SR00814DE): Installation of Garmin Helicopter Terrain Awareness and Warning System (HTAWS). Cert Works LLC - [STC SR01812LA](https://openairdocs.org/stc/SR01812LA): Installation of Apical Industries, Inc. Emergency Float Kit.. Apical Industries Inc. dba Dart Aerospace - [STC SR02257CH](https://openairdocs.org/stc/SR02257CH): Install air ambulance conversion. Snaky Creek Enterprises LLC dba Spectrum Aeromed - [STC SR02894CH](https://openairdocs.org/stc/SR02894CH): Install EMS ITS Deck with the Factory EMS Interior. Spectrum Aeromed LLC dba Spectrum Aeromed - [STC SR02974CH](https://openairdocs.org/stc/SR02974CH): Install air ambulance conversion. Spectrum Aeromed LLC dba Spectrum Aeromed - [STC SR02977CH](https://openairdocs.org/stc/SR02977CH): Install of a medical floor liner. Spectrum Aeromed LLC dba Spectrum Aeromed - [STC SR02978CH](https://openairdocs.org/stc/SR02978CH): Install of Shore Power Mechanical Provisions. Spectrum Aeromed LLC dba Spectrum Aeromed - [STC SR02980CH](https://openairdocs.org/stc/SR02980CH): Install of an interior panel system. Spectrum Aeromed LLC dba Spectrum Aeromed All 185: https://openairdocs.org/tcds/H7EU/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.