TCDS H10EU

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET No. H10EU This data sheet which is a part of type certificate No. H10EU prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Airbus Helicopters Aéroport International Marseille Provence 13725 - Marignane - Cedex France TC Holder Record: Eurocopter France changed name to Airbus Helicopters on January 1, 2014. Engine. 2 Turbomeca Arriel 1A Engine Limits. (Sea level static - standard day conditions) Power shaft Gas generator Exhaust Gas Temp. T4 2½ min. power rating 651 shp (486 Kw) 52,700 rpm 840°C 30 min. power rating 625 shp (466 Kw) 52,000 rpm 810°C Takeoff (min.) 625 shp (466 Kw) 52,000 rpm 810°C Maximum continuous 576 shp (430 Kw) 50,750 rpm 775°C Starting (5 sec. max.) 840°C Starting (without limit) 775°C Eng. gearbox limitations 699 shp (521 Kw) @ 350 Rotor rpm 100% Ng = 51,800 rpm Transmission Limits. Maximum (one eng. inoperative) 701 shp (523 Kw) (at 350 Rotor rpm) Maximum Takeoff (5 min.) 503 shp (375 Kw) per engine (See NOTE 5 & 6) Maximum Continuous OR Maximum Takeoff (5 min.) 469 shp (350 Kw) per engine 577 shp (430 Kw) per engine Maximum Continuous 532 shp (397 Kw) per engine H10EU Revision 22 Airbus Helicopters AS 365 N2 AS 365 N3 EC 155 B EC 155 B1 SA 365 C SA 365 C1 SA 365 C2 SA 365 N SA 365 N1 SA 366 G1 July 9, 2026 I. Model SA 365 C “Dauphin” (Transport Helicopter, Category B), approved October 11, 1978. Model SA 365 C “Dauphin” (Transport Helicopter, Category A), approved May 4, 1979. Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Rev. No. 22 22 22 22 22 14 22 22 17 22 16 22 22 22 22 22 Page 2 of 16 H10EU Helicopter Limits. Maximum (one eng. inoperative) 699 shp (521 Kw) (torque 109%) (at 350 Rotor rpm) Maximum Takeoff (5 min.) 503 shp (375 Kw) per engine (torque 78%) (See NOTE 5 & 6) Maximum Continuous 469 shp (350 Kw) per engine (torque 73%) OR Maximum Takeoff (5 min.) 577 shp (430 Kw) per engine (torque 90%) Maximum Continuous 532 shp (397 Kw) per engine (torque 83%) C.G. Range. Longitudinal : + 151.1 in. to 161.4 in. Lateral : Right: 4.3 in. Left : 4.3 in. Maximum Weight. 7,500 lbs The Model SA 365 C1 is identical to the Model SA 365 C except for engine model and engine limits. Engine. 2 Turbomeca Arriel 1A1 Engine Limits. (Sea level static - standard day conditions) Power shaft Gas generator Exhaust Gas Temp. shp (Kw) rpm T4 °C 2½ min. power rating 667 (498) 52,900 840 30 min. power rating 643 (480) 52,250 810 Takeoff (min.) 630 (470) 52,000 810 Maximum continuous 579 (432) 50,750 775 Starting (5 sec. max.) 840 Starting (without limit) 775 Eng. gearbox limitations 699 shp (521 Kw) @ 350 Rotor rpm 100% Ng = 51,800 rpm Transmission Limits. Maximum (one eng. inoperative) 701 shp (523 Kw) (at 350 Rotor rpm) Maximum Takeoff (5 min.) 503 shp (375 Kw) per engine (See NOTE 5 & 6) Maximum Continuous 469 shp (350 Kw) per engine OR Maximum Takeoff (5 min.) 577 shp (430 Kw) per engine Maximum Continuous 532 shp (397 Kw) per engine Helicopter Limits. Maximum (one eng. inoperative) 699 shp (521 Kw) (torque 109%) (at 350 Rotor rpm) Maximum Takeoff (5 min.) 503 shp (375 Kw) per engine (torque 78%) (See NOTE 6) Maximum Continuous 469 shp (350 Kw) per engine (torque 73%) OR Maximum Takeoff (5 min.) 577 shp (430 Kw) per engine (torque 90%) Maximum Continuous 532 shp (397 Kw) per engine (torque 83%) C.G. Range. Longitudinal : + 151.1 in. to 161.4 in. Lateral : Right: 4.3 in. Left : 4.3 in. Maximum Weight. 7,500 lbs II. Model SA 365 C1 “Dauphin” (Transport Helicopter, Category B), approved August 9, 1979 (See NOTE 5). Model SA 365 C1 “Dauphin” (Transport Helicopter, Category A), approved October 5, 1979 (See NOTE 5). Page 3 of 16 H10EU The Model SA 365 C2 differs from SA 365 C1 in engine model and limits; gross weight and C.G. range; transmission rating and transmission and helicopter limits. Engine. 2 Turbomeca Arriel 1A2 Engine Limits. (Sea level static - standard day conditions) Power shaft Gas generator Exhaust Gas Temp. shp (Kw) rpm T4 °C 2½ min. power rating 670 (500) 52,900 840 30 min. power rating 657 (490) 52,550 810 Takeoff (min.) 630 (470) 52,000 810 Maximum continuous 579 (432) 50,750 775 Starting (5 sec. max.) 840 Starting (without limit) 775 Eng. gearbox limitations 699 shp (521 Kw) @ 350 Kw Rotor rpm 100% Ng = 51,800 rpm Transmission Limits. Maximum (one eng. inoperative) 701 shp (523 Kw) (at 350 Rotor rpm) Maximum Takeoff (5 min.) 577 shp (430 Kw) per engine Maximum Continuous 532 shp (397 Kw) per engine Helicopter Limits. Maximum (one eng. inoperative) 699 shp (521 Kw) (torque 109%) (at 350 Rotor rpm) Maximum Takeoff (5 min.) 577 shp (430 Kw) per engine (torque 90%) Maximum Continuous 532 shp (397 Kw) per engine (torque 83%) C.G. Range. Longitudinal: + 151.1 in. to + 161.4 in. up to 7500 lb. + 151.1 in. to + 159.8 in. from 7500 lb to 7715 lb. Lateral: Right: 4.3 in. Left: 4.3 in. Maximum Weight. 7,715 lbs The Model SA 365 N differs from SA 365 C2 in engine model and limits; gross weight and C.G. range; transmission rating and transmission and helicopter limits. Engine. 2 Turbomeca Arriel 1C Engine Limits. (Sea level static - standard day conditions) Power shaft Gas generator Exhaust Gas Temp. shp (Kw) rpm T4 °C 2½ min. power rating 700 (522) 53,199 860 30 min. power rating 686 (512) 52,318 835 Takeoff (min.) 659 (492) 51,800 835 Maximum continuous 586 (437) 50,505 785 Starting (5 sec.max.) 860 Starting (without limit) 785 Eng. gearbox limitations 739 shp (551.5 kw) @ 350 Rotor rpm 100% Ng = 51,800 rpm III. Model SA 365 C2 “Dauphin” (Transport Helicopter, Category A and B), approved April 24, 1980. IV. Model SA 365 N “Dauphin” (Transport Helicopter, Category A and B), approved November 20, 1981. Page 4 of 16 H10EU Transmission Limits. Maximum (one eng. inoperative) 737 (523) (at 350 Rotor rpm Maximum Takeoff (5 min.) 603 (450) shp (xxxKw) per engine Maximum Continuous 567 (423) Helicopter Limits. Maximum (one eng. inoperative) 737 (550 Kw) (torque 1 or 2: 61%) (at 350 Rotor rpm) Maximum Takeoff (5 min.) 603 (450 Kw) (torque 1 + 2: 100%) shp (xxxKw) per engine Maximum Continuous 567 (423 Kw) (torque 1 + 2: 94%) C.G. Range. Longitudinal: Lateral: Right 2.95 in. Left 2.95 in. Maximum Weight. 8,818 lbs The Model SA 365 N1 differs from SA 365 N in engine model and limits; gross weight and tail boom change. Engine. 2 Turbomeca Arriel 1C1 Engine Limits. (Sea level static - standard day conditions) Power shaft Gas generator Exhaust Gas Temp. shp (Kw) rpm T4 °C 2½ min. power rating 724 (540) 52,940 865 30 min. power rating 705 (526) 52,215 845 Takeoff (min.) 705 (526) 52,215 845 Maximum continuous 586 (437) 50,246 775 Starting (5 sec.max.) 865 Starting (without limit) 785 Eng. gearbox limitations 739 shp (551.5 Kw) @ 350 Kw Rotor rpm 100% Ng = 51,800 rpm V. Model SA 365 N1 “Dauphin” (Transport Helicopter, Category A and B), approved December 1, 1986. Page 5 of 16 H10EU Transmission Limits. Maximum (one eng. inoperative) 737 (550) (at 350 Rotor rpm) Maximum Takeoff (5 min.) 603 (450) shp (xxxKw) per engine Maximum Continuous 567 (423) Helicopter Limits. Maximum (one eng. inoperative) 737 (550 Kw) (torque 1 or 2 : 61%) Maximum Takeoff (5 min.) 603 (450 Kw) (torque 1 + 2: 100%) Maximum Continuous 567 (423 Kw) (torque 1 + 2: 94%) C.G. Range. Longitudinal: Maximum Weight. 9,038 lbs The Model AS 365 N2 differs from SA 365 N1 in engine model and limits; gross weight and main gearbox torque. Engine. 2 Turbomeca Arriel 1C2 Engine Limits. (Sea level static - standard day conditions) Power shaft Gas generator Exhaust Gas Temp. shp (Kw) rpm T4 °C 2½ min. power rating 712 (531) 52,328 885 30 min. power rating 712 (531) 52,328 845 Takeoff (min.) 712 (531) 52,328 845 Maximum continuous 632 (471) 50,867 775 Starting (5 sec. max.) 865 Starting (without limit) 785 Eng. gearbox limitations 739 shp (551.5 Kw) @ 350 Rotor rpm 100% Ng = 51,800 rpm VI. Model AS 365 N2 “Dauphin” (Transport Helicopter, Category A and B), approved October 31, 1990. Page 6 of 16 H10EU Transmission Limits. Maximum (one eng. inoperative) 737 (550) (at 350 Rotor rpm) Maximum Takeoff (5 min.) 647 (482,5) shp (xxxKw) per engine Maximum Continuous 567 (423) Helicopter Limits. Maximum (one eng. inoperative) 737 (550 Kw) (torque 1 or 2 : 57%) Maximum Takeoff (5 min.) 647 (482,5 Kw) (torque 1 + 2: 100%) Maximum Continuous 567 (423 Kw) (torque 1 + 2: 98%) C.G. Range. Longitudinal: Lateral: Right: 2.95 in. Left : 2.95 in. Right: 1.96 in. Left : 1.96 in. Up to 4100 Kg Beyond 4100 Kg Maximum Weight. 9,370 lbs Engine. 2 Avco Lycoming LTS 101-750B-2 (See NOTE 10) VII. Model SA-366G1 “Dauphin” (Transport Helicopter, Category A and B), approved July 28, 1983. Page 7 of 16 H10EU Installed Engine Limits. (See NOTE 9 & 10) Output Shaft Torque % (ft-lbs) Gas Generator Speed-N1 % (rpm) Output Shaft Speed-N2 % (rpm) Measured Gas Temperature °C (°F) Normal Operation: (Torque 1 + 2) Takeoff power (5 min.) 100 (1056) 104.1 (49830) 102.3 (6138) 786 (1447) Max. Continuous 94 (993) 102.9 (49255) 102.3 (6138) 765 (1409) One Engine Inoperative: (Torque 1 or 2) 2.5 min. power 100 (643) 106.1 (50787) 102.3 (6138) 822 (1512) 30 min. power 95.5 (614) 104.8 (50169) 102.3 (6138) 800 (1471) Max. Continuous 88.2 (567) 102.9 (49255) 102.3 (6138) 765 (1409) Refer to Rotorcraft Flight Manual for other limitations including speed and temperature transients. C.G. Range. Longitudinal: + 151.1 in. to 157.5 in. Lateral : Right 5.62 in. Left 3.93 in. Maximum Operating Altitude. 18,000 feet pressure altitude Maximum Weight. 8,950 lbs The Model AS 365 N3 differs from AS 365 N2 in engine model and limits. Engine. 2 Turbomeca Arriel 2C engines Engine Limits. (Sea level static - standard day conditions) Power shaft Gas generator Exhaust Gas Temp. shp (Kw) rpm T4 °C 30 sec. OEI rating 944 (704) 55,051 1000 2 min. OEI rating 851 (635) 53,192 941 Continuous OEI 818 (610) 52,571 912 Takeoff (5 min.) 779 (581) 52660 912 Maximum continuous 779 (581) 51520 877 Starting (10 sec. max.) 865 Starting (without limit) 750 100% Ng = 52,110 rpm Transmission Limits. Maximum continuous (OEI) 815 (608 Kw) (torque 1 or 2 : 63%) (@ 350 rpm) Maximum Takeoff (5 min.) 1294 (965 Kw) (torque 1 + 2: 100%) Maximum Continuous 1138 (849 Kw) (torque 1 + 2: 88%) VIII. Model AS 365 N3 “Dauphin” (Transport Helicopter, Category A and B), approved November 6, 1998. Page 8 of 16 H10EU C.G. Range. Longitudinal: Lateral: Right: 2.95 in. Left : 2.95 in. Right: 1.96 in. Left : 1.96 in. Up to 4100 Kg Beyond 4100 Kg Maximum Weight. 9,370 lbs The Model EC 155 B is a derivative of the AS 365 N3 and incorporates an increase in gross weight, enlarged fuselage structure, a new 5-blade main rotor, a fenestron with RTM technology, and a new avionics and AFCS system. Engine. 2 Turbomeca Arriel 2C1 engines Engine Limits. (Sea level static - standard day conditions) Power shaft Gas generator Exhaust Gas Temp. shp (Kw) rpm T4 °C 30 sec. OEI rating 962 (718) 54,986 1000 2 min. OEI rating 865 (646) 53,126 941 Continuous OEI 833 (622) 52,506 912 Takeoff (5 min.) 779 (581) 52,776 912 Maximum continuous 779 (581) 51,637 877 Starting (10 sec. max.) 865 Starting (without limit) 750 100% Ng = 52,110 rpm Transmission Limits. Refer to Rotorcraft Flight Manual IX. Model EC 155 B “Dauphin” (Transport Helicopter, Category A and B), approved December 14, 2000. Page 9 of 16 H10EU C.G. Range. Longitudinal: Lateral: LH Limit –1.97 inches RH Limit +1.97 inches Datum: 157.5 inches (4 m forward of the main rotor center line) longitudinal Aircraft symmetry plane lateral Maximum Weight. 10,582 lbs (4800 kg) Maximum Altitudes. Refer to Rotorcraft Flight Manual Airspeed Limits. Power on - 175 KIAS (refer to flight manual for reduction as a function of altitude) Power off - 135 KIAS (refer to flight manual for reduction as a function of altitude) Rotor Speeds. Power on flight: 342-350 rpm (governed speed range) Power off flight: Maximum Transient: 390 rpm Maximum Steady State: 375 rpm Minimum: 316 rpm Minimum Transient: 295 rpm Minimum Flight Crew. One Pilot in the Right Hand Seat Maximum Seating Capacity. 15 (including pilot seat) Emergency Exits. 3 Type IV exits on each side of fuselage Fuel. Refer to Rotorcraft Flight Manual Engine Oil. Refer to Rotorcraft Flight Manual MGB and TGB oil. MIL-L-6086 (Mineral oil) Fuel Capacity. Total 338 gallons (1280 litres) Usable 332 gallons (1256.5 litres) Unusable 6 gallons (23.5 litres) Oil Capacity. Engine oil 2 x 6.2 liters (normal level) MGB 9 liters (max) TGB 0.5 liters (max) Serial Numbers eligible. S/N 6544 and up (See NOTE 12) Page 10 of 16 H10EU The Model EC 155 B1 is a derivative of the EC 155 B and incorporates the Turbomeca Arriel 2C2 engines. Engine. 2 Turbomeca Arriel 2C2 engines Engine Limits. (Sea level static - standard day conditions) Power shaft Gas generator Exhaust Gas Temp. shp (Kw) rpm T4 °C 30 sec. OEI rating 1006 (750) 55265 996 2 min. OEI rating 956 (713) 53275 944 Continuous OEI 858 (640) 52764 926 Takeoff (5 min.) 821 (612) 53079 929 Maximum continuous Starting (10 sec. max.) Starting (without limit) 821 (612) 51922 891 840 100% Ng = 52,110 rpm Transmission Limits. Refer to Rotorcraft Flight Manual C.G. Range. Longitudinal: Lateral: LH Limit –1.97 inches RH Limit +1.97 inches Datum: 157.5 inches (4 m forward of the main rotor center line) longitudinal Aircraft symmetry plane lateral Maximum Weight. 10,692 lbs (4850 kg) Maximum Altitudes. Refer to Rotorcraft Flight Manual Airspeed Limits. Power on - 175 KIAS (refer to flight manual for reduction as a function of altitude) Power off - 135 KIAS (refer to flight manual for reduction as a function of altitude) X. Model EC 155 B1 “Dauphin” (Transport Helicopter, Category A and B), approved June 3, 2003. Page 11 of 16 H10EU Rotor Speeds. Power on flight: 342-350 rpm (governed speed range) Power off flight: Maximum Transient: 390 rpm Maximum steady State: 375 rpm Minimum: 316 rpm Minimum Transient: 295 rpm Minimum Flight Crew. One Pilot in the Right Hand Seat Maximum Seating Capacity. 15 (including pilot seat) Emergency Exits. 3 Type IV exits on each side of fuselage Fuel. Refer to Rotorcraft Flight Manual Engine Oil. Refer to Rotorcraft Flight Manual MGB and TGB oil. MIL-L-6086 (Mineral oil) Fuel Capacity. Total 338 gallons (1280 litres) Usable 332 gallons (1256.5 litres) Unusable 6 gallons (23.5 litres) Oil Capacity. Engine oil 2 x 6.2 litres (normal level) MGB 9 litres (max) TGB 0.5 litres (max) Serial Numbers eligible. S/N 6620 and up Page 12 of 16 H10EU DATA PERTINENT TO ALL MODELS. Fuel. Rotor Speeds (rpm). Refer to Rotorcraft Flight Manual SA 365 C SA 365 N SA 366 G1 AS 365 N2 AS 365 N3 SA 365 N1 In autorotation Maximum transient - 420 420 420 420 Maximum 420 395 395 395 395 Minimum 320 320 320 320 320 Minimum transient 285 295 295 295 295 In power-on flight All Engines Operating 350±10 350+15 350+8 350±10 355-360 - 10 -10 One Engine Inoperative 320 (min) 320 340 320 320 Speed Warning Low speed 338 335 335 335 345 (aural) High speed 400 380 380 380 380 (See NOTE 10) Airspeed Limits. Kts - IAS Never exceed speed VNE: 170* 175* (6614) (6614) 165* 175* (6614) (6614) * At sea level and gross weight (XXXX) lbs. Refer to Helicopter Flight Manual for decrease with weight and altitude. Minimum Crew. SA 365 C Series SA 365 N SA 366 G1 AS 365 N3 AS 365 N2 SA 365 N1 1 pilot 1 1 1 Maximum Passengers. SA 365 C Series SA 365 N SA 366 G1 AS 365 N3 AS 365 N2 SA 365 N1 13 13 2 13 Maximum Baggage. Refer to Rotorcraft Flight Manual Fuel/Oil Capacity. U.S. gals (moment arm in.) SA 365 C Series SA 365 N SA 366 G1 AS 365 N3 AS 365 N2 SA 365 N1 Fuel: Maximum 169/(147.6) 306/(156.1) 289.8 (156.3) 306/(156.3) usable 168.3 303 285.6 302.7 unusable See NOTE 1 See NOTE 1 See NOTE 1 See NOTE 1 Oil: engine x 1.8 (232.3) 2 x 1.37 (160.5) 2 x 1.32 (160.5) 2 x 1.37 (160.5) transmission 2.8 (160.6) 2.4 (160.6) 2.4 (160.6) 2.8 (160.6) tail rotor 0.07 (407.9) 0.13 (410.6) 0.053 (417) 0.053 (417) Empty Weight C.G. Range. None None None None Datum. 157.4* 157.4* 157.4* 157.4* * in forward of main rotor hub center Leveling Means. Three plates on the left side of transmission support platform. Rotor Blades and For rigging information refer to the Maintenance Manual appropriate to Model. Control Movements. Serial Numbers Eligible. The French Government “Certificate de Navigabilite pour Exportation” and as noted below under “Import Requirements” must be submitted for each individual aircraft for which application for FAA certification is made. Page 13 of 16 H10EU Certification Basis. Model SA 365 C Series: FAR 21.29 and FAR 29 effective February 1, 1965 plus amendments 29-1 through 29-11 plus FAA Special Conditions No.29-69-EU-21, dated April 6, 1976. The Airworthiness Criteria for Helicopter Instrument Flight, dated December 15, 1978, for IFR certification. Models SA 365 N, SA 366 G1, SA 365 N1, AS 365 N2: FAR 21.29 and FAR 29 effective February 11, 1965, plus amendments 29-1 through 29-11. In addition applicant elected to comply with FAR 29 amendments 29-12 through 29-16 except for FAR 29.397 as concerns rotorbrake. The Airworthiness Criteria for Helicopter Instrument Flight, dated December 15, 1978, for IFR certification. Model AS 365 N3: FAR 21.29 and FAR 29 effective February 11, 1965, plus amendments 29-1 through 29-16. In addition, FAA Special Condition number 29-002-SC for HIRF. Equivalent Safety Findings - For Model SA 365 N1 and AS 365 N2: Longitudinal Static Stability FAR 29.173 For Model SA 366 G1: Plenum air intake meets the ice protection of FAR 29.1093(b) Amendment 29-22. Model EC 155 B and Model EC 155 B1 FAR 21.29 and FAR 29 Amendment 29-1 through Amendment 29-40 with the following exceptions: - Excluding Amendment 29-38 (Occupant Protection) - Excluding FAR 29.952 introduced at Amendment 29-35 (CRFS) - Excluding FAR 29.562 introduced at Amendment 29-29 - Excluding FAR 29.631 introduced at Amendment 29-40 - FAR 29.561(a), (b), and (d) at Amendment 29-1 - FAR 29.561(c) at Amendment 29-29 - FAR 29.571 at Amendment 29-20 - FAR 29.571 at Amendment 29-28 fatigue evaluation composites and new metallics) - FAR 29.785 at Amendment 29-24 - FAR 29.901 at Amendment 29-26 - FAR 29.903 at Amendment 29-31 - FARs 29.963, 29.973, and 29.975 at Amendment 29-26 - FAR 29.1305(a)(4)(i) at Amendment 29-16 - FAR 36 Appendix H through the latest amendment 36-20 - Special Condition 29-007-SC for HIRF - Equivalent level of safety findings: FAR 29.723, 29.725, and 29.727 Landing Gear Drop Test FAR 29.807(c) Passenger Emergency Exits; other than side of fuselage FAR 29.173 and 29.175 Static Longitudinal Stability FAR 29, Appendix B Section IV Return to trim characteristics Page 14 of 16 H10EU Certification Basis. (Cont’d) Type Certificate No. H10EU issued October 11, 1978. Date of application for Type Certificate: SA 365 C Model, November 20, 1974 SA 365 C1 Model, April 6, 1979 SA 365 C2 Model, October 12, 1979 SA 365 N Model, April 9, 1979 SA 366 G1 Model, August 3, 1982 SA 365 N1 Model, February 17, 1981 AS 365 N2 Model, February 21, 1989 AS 365 N3 Model, June 18, 1997 EC 155 B Model, September 1, 1998 The French Direction Generale de l’Aviation Civile (DGAC) originally type certificated this rotorcraft under its type certificate TC 86. The FAA validated this product under U.S. Type Certificate Number H10EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the DGAC. Noise Standards. Models AS 365 N2 and AS 365 N3 FAR 36 as amended by amendment 36-1 through 36-16. Import Requirements. The FAA can issue a U.S. airworthiness certificate based on a National Aviation Authority (NAA) Export Certificate of Airworthiness (Export C of A) signed by a representative of the French Generale de l’Aviation Civile (DGAC) 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 type design approved under U.S. Type Certificate Number H10EU 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. The type designs approved under TC H10EU are defined by Aerospatiale Documents: 365A.04.3215 and 365A.05.0408 for Model SA 365 C 365A.05.0416 for Model SA 365 C1 365A.05.0426 for Model SA 365 C2 365A.05.0430 for Model SA 365 N 366A.04.3237 for Model SA 366 G1 (See NOTE 10) 365ABN.0017 Issue A for Model SA 365 N1 365ABN.0017 Issue B for Model AS 365 N2 365ABN.0017 Issue C for Model SA 365 N3 365ABN0104 for Model EC 155 B 365A.04.6840 for Model EC 155 B1 Service Information. 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 French Generale de l’Aviation Civile (DGAC). 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 the type design data. Page 15 of 16 H10EU Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the helicopter for certification. Required and Optional Equipment SA 365 C SA 365 N/N1 SA 366 G1 AS 365 N2 Aerospatiale Report: 365A04.3265 365A04.3075 365A04.3983 366A04.3094 365A04.4689 Electronic and Navigation Equipment 365A04.3228 365A04.3422 366A04.3079 365A04.4693 In addition, the following item of equipment is required: DGAC-approved Helicopter Flight Manual, Code B, approved December 12, 1978, for Model SA 365 C. DGAC-approved Helicopter Flight Manual, Code B, approved August 9, 1979, for Model SA 365 C1. DGAC-approved Helicopter Flight Manual, Code B, approved February 18, 1980, for Model SA 365 C2. DGAC-approved Helicopter Flight Manual, Code B, approved September 25, 1981, for Model SA 365 N. DGAC-approved Helicopter Flight Manual, Code B, Normal Revision, approved July 20, 1983, or later approved revisions for Model SA 366 G1. DGAC-approved Helicopter Flight Manual, Code B, with RR2A(86-03) and RR2B(86-46) approved December 1, 1986, or later approved revisions for Model SA 365 N1. DGAC-approved Helicopter Flight Manual, Code B, approved October 31, 1990, for Model AS 365 N2. DGAC-approved Helicopter Flight Manual, Code B, approved December 18, 1997, for Model AS 365 N3. DGAC-approved Helicopter Flight Manual, Issue 4 plus Rush Revisions 5A and 5B,