TCDS.R.123 Page 1 of 22 European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET SE 3160 SA 316B SA 316C SA 319B SA 315B Type Certificate Holder: Eurocopter Aéroport International Marseille Provence 13725 Marignane cedex France Manufacturer: Eurocopter Aéroport International Marseille Provence 13725 Marignane cedex France Issue 1: 27 January, 2010 List of effective Pages: Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 Issue 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1
TCDS.R.123 Page 2 of 22 TABLE OF CONTENTS Section Page SE 3160 & SA 316B I General 3 II Certification Basis 3 III Technical Characteristics and Operational Limitations 4 IV Operating and Service Instructions 7 V Notes 7 SA 316C I General 8 II Certification Basis 8 III Technical Characteristics and Operational Limitations 9 IV Operating and Service Instructions 12 V Notes 12 SA 319B I General 13 II Certification Basis 13 III Technical Characteristics and Operational Limitations 14 IV Operating and Service Instructions 17 V Notes 17 SA 315B I General 18 II Certification Basis 18 III Technical Characteristics and Operational Limitations 19 IV Operating and Service Instructions 22 V Notes 22
TCDS.R.123 Page 3 of 22 SE 3160 & SA 316B I. General 1. Data Sheet No: EASA.R.123 Corresponding to DGAC-F n 61, issue 7 dated March 1993 2. Type / Variant or Model: (a) Type: SE 316 (b) Variant or Model: SE 3160, SA 316B 3. Airworthiness Category: Small Rotorcraft 4. Type Certificate Holder: Since June 1, 1997 Before June 1, 1997 EUROCOPTER Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE EUROCOPTER FRANCE Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE Between January 1, 1970 and January 1, 1992 AEROSPATIALE 37, Boulevard de Montmorency 75781 PARIS cedex 16 FRANCE Before January 1, 1970 SUD AVIATION 37, Boulevard de Montmorency 75016 PARIS - FRANCE 5. Manufacturer: As above 6. National Certification Date: SE 3160 December 15, 1961 SA 316B March 17, 1970 (DGAC-F National TC N 14) 7. DGAC-F Application Date: N/A 8. DGAC-F Recommendation Date: N/A 9. EASA Certification Date: N/A II. Certification Basis 1. Certification Basis: CAR-6, edition dated December 20, 1956 (including 6-1 to 6-3 amdt) with additional Special Conditions for turbine Helicopter notified at the French DGAC by the government of the United States (FAA letter dated May 03, 1960) 2. Airworthiness Requirements: As defined above 3. Reversions and Exemptions Granted: N/A 4. Equivalent Safety Findings: N/A 5. Special Conditions: Refer to 1 certification basis
TCDS.R.123 Page 4 of 22 6. Environmental Standards including noise: N/A III. Technical Characteristics and Operational Limitations 1. Type Design Definition: SE 3160: basic SE 3160 definition SA 316B: definition of SA 316B is obtained by applying to the SE 3160 modifications (structural reinforcements and mechanical assy. Improvement) which allows extending the maximal weight. All SE 3160 aircrafts could be improved to SA 316B version by applying Aérospatiale Service Bulletin Alouette N 01-20. 2. Description: Small single-engine helicopter. 3. Equipment: As per compliance with applicable airworthiness requirements defined here above and referenced within approved Flight Manual. 4. Dimensions: Fuselage: Length: 10,175 m (33,38 ft) Width: Height: 2,590 m (8,50 ft) for H/C equipped with wheel gear 2,650 m (8,69 ft) for H/C equipped with skid gear 3,920 m (12,86 ft) for H/C equipped with float gear 2,970 m (9,74 ft) 3,460 m (11,35 ft) for H/C equipped with float gear Main Rotor: 3 blades Diameter: 11,000 m (36,09 ft) Tail Rotor: 3 blades Diameter: 1,912 m (6,27 ft) 5. Engines: SE 3160, SA 316B 1 Turboméca ARTOUSTE III B or III B1 see DGAC-F engine TC M12 5.1 Installed Engine Limits: - max Rpm: 33500 rpm ± 200 (±1000 rpm during transitory variation allowed) - max power at Take-off: - 640 kw (thermic) on ground - 420 kw (reducer) with ARTOUSTE III B - 440 kw (reducer) with ARTOUSTE III B1 - max continuous power used: 405 kw (reducer) - max T4 temperature at engine start: 630 C - max T4 temperature continuous: 500 C - max T4 temperature (5 ): 550 C 5.2 Transmission Torque Limits: - Take-off power: 405 kw (SE 3160) / 440 kw (SA 316B) - Max continuous power: 331 kw (SE 3160 & SA 316B) 6. Fluids (Fuel/Oil/Hydraulic/Additives): 6.1 Fuel: as approved in the Flight Manual 6.2 Oil: as approved in the Flight Manual for engine and gearboxes 6.3 Hydraulic: as approved in the Flight Manual 6.4 Additives: as approved in the Flight Manual
TCDS.R.123 Page 5 of 22 7. Fluid Capacities: 7.1 Fuel: cubic tank: 565 l ± 3,13 (149,2 US Gal ± 0,82) usable in flight 555 l (146,6 US Gal) (total tank capacity: 595 l (157,1 US Gal) quadrilobic tank: 575 l ± 3,13 (151,9 US Gal ± 0,82) usable in flight 573 l (151,3 US Gal) (total tank capacity: 590 l (155,8 US Gal) 7.2 Oil: 10 l ± 3,62 (2,64 US Gal ± 0,95) 8. Airspeed Limits: - For centre of gravity between 2,78 m and 3,08 m: - SE 3160 & SA 316B (for instruments with metric measures indications): Altitude (m) 0 to 1000 2000 3000 4000 5000 6000 Weight (kg) 2200* 210 2100 210 1900 210 1700 210 1500 210 * SA 316 B only 195 200 207 210 210 Vne (km/h) 172 180 140 188 160 195 173 203 185 115 143 160 - SE 3160 (for instruments with imperial measures indications): 105 130 Altitude (ft) 0 to 3000 6000 9000 12000 15000 18000 21000 Weight -(lb) S Vne (kt) 4630 A 109 101 85 4400 110 103 89 4000 3 112 106 94 79 58 3600 f 108 99 86 72 51 3300 110 102 92 78 62 ( - SA 316B (for instruments with imperial measures indication): Altitude (ft) 0 to 3000 6000 9000 12000 15000 18000 21000 Weight (lb) 4850 4630 4200 3750 3300 107 109 111 97 101 104 107 110 Vne (kt) 85 92 97 102 75 84 92 50 68 78 45 62 - For centre of gravity between 3,08 m and 3,15 m (single-seat flight): - Instruments with metric measures indications: same limitation as above but Vne limited to 190 km/h. - Instruments with imperial measures indications: same limitation as above but Vne limited to 103 kt.
TCDS.R.123 Page 6 of 22 9. Rotor Speed Limits: - Max rotor speed: 420 rpm - Min rotor speed: 270 rpm - Max continuous rotor speed: 353 rpm 10. Maximum Operating Altitude and Temperature: 10.1 Altitude: Flight: 6500m (21300 ft) Start: 5800m (19000 ft) 10.2 Temperature: - 40 C to + 55 C 11. Operating Limitations: VFR day VFR night when the additional equipment required by operational regulations is installed and serviceable. (For more information refer to approved Flight Manual) 12. Maximum Certified Weights: Take-off and landing: SE 3160 2100kg (4629,7 lb) SE 316B 2200kg (4850,1 lb) 13. Centre of Gravity Range: Longitudinal: Forward limit: 2,78 m Aft limit: 3,08 m Or Forward limit: 3,08 m with the following speed limitation: Aft limit: 3,15 m Maximum translation speed: - For centre of gravity between 2,80 m and 3,08 m: 210 km/h ( kt) - For centre of gravity between 3,08 m and 3,15 m: 190 km/h (103 kt) Lateral: Left limit: 0,14 m Right limit: 0,12 m 14. Datum: Longitudinal: Lateral: 3 m (9,84 ft) forward of main rotor centreline aircraft symmetry plane 15. Levelling Means: 4 levelling legs on the central structure: - 2 on the front of the aircraft - 2 on the rear of the aircraft 16. Minimum Flight Crew: 1 pilot 17. Maximum Passenger Seating Capacity: 6 Front seats: 2 passengers Rear seats: 4 passengers 18. Passenger Emergency Exits: Refer to approved Flight Manual 19. Maximum Baggage/Cargo Loads: Refer to approved Flight Manual 20. Rotor Blade and Control Movement: Refer to aircraft Maintenance Manual 21. Auxiliary Power Unit: None
TCDS.R.123 Page 7 of 22 IV. Operating and Service Instructions 1. Rotorcraft Flight Manual, Document No: SE 3160 and SA 316B Flight Manual original edition approved by DGAC-F for type certification, or later DGAC-F or EASA approved revision. 2. Maintenance Manual, Document No: SE 3160 and SA 316B Maintenance Manual. 3. Service Letters and Service Bulletins: As published by Aérospatiale or Eurocopter and approved by DGAC-F or EASA 4. Required Equipment: As per compliance with applicable requirements and in accordance with the original Type Design standard; refer to approved Flight Manual. 5. Master Minimum Equipment List: None V. Notes 1. Eligible serial numbers: 1048 and subsequent 2. The certified optional installations are each approved independently of the basic helicopter and an approved Flight Manual Supplement is associated to each optional installation if necessary. 3. Commercial designation: ALOUETTE III
TCDS.R.123 Page 8 of 22 SA 316C I. General 1. Data Sheet No: EASA.R.123 Corresponding to DGAC-F n 61, issue 7 dated March 1993 2. Type / Variant or Model: (a) Type: SE 316 (b) Variant or Model: SA 316C 3. Airworthiness Category: Small Rotorcraft 4. Type Certificate Holder: Since June 1, 1997 Before June 1, 1997 EUROCOPTER Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE EUROCOPTER FRANCE Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE Between January 1, 1970 and January 1, 1992 AEROSPATIALE 37, Boulevard de Montmorency 75781 PARIS cedex 16 FRANCE Before January 1, 1970 SUD AVIATION 37, Boulevard de Montmorency 75016 PARIS FRANCE 5. Manufacturer: As above 6. National Certification Date: SA 316C May 14, 1971 (DGAC-F National TC N 14) 7. DGAC-F Application Date: N/A 8. DGAC-F Recommendation Date: N/A 9. EASA Certification Date: N/A II. Certification Basis 1. Certification Basis: CAR-6, edition dated December 20, 1956 (including 6-1 to 6-3 amdt) with additional Special Conditions for turbine Helicopter notified at the French DGAC by the government of the United States (FAA letter dated May 03, 1960) 2. Airworthiness Requirements: As defined above 3. Reversions and Exemptions Granted: N/A 4. Equivalent Safety Findings: N/A 5. Special Conditions: Refer to 1 certification basis 6. Environmental Standards including noise: N/A
TCDS.R.123 Page 9 of 22 III. Technical Characteristics and Operational Limitations 1. Type Design Definition: SA 316C: definition of SA 316C is obtained by applying to the SE 3160 modifications according to document Aérospatiale SA 319 A 04.00.025 2. Description: Small single-engine helicopter. 3. Equipment: As per compliance with applicable airworthiness requirements defined here above and referenced within approved Flight Manual. 4. Dimensions: Fuselage: Length: 10,175 m (33,38 ft) Width: 2,602 m (8,54 ft) Height: 3,000 m (9,84 ft) Main Rotor: 3 blades Diameter: 11,020 m (36,15 ft) Tail Rotor: 3 blades Diameter: 1,920 m (6,30 ft) 5. Engines: 1 Turboméca ARTOUSTE III D see DGAC-F engine TC M12 5.1 Installed Engine Limits: - max Rpm: 33500 rpm ± 200 (±1000 rpm during transitory variation allowed) - max power at Take-off: - 640 kw (thermic) on ground - 440 kw (reducer) - max continuous power used: 405 kw (reducer) - max T4 temperature at engine start: 630 C - max T4 temperature continuous: 500 C - max T4 temperature (5 ): 550 C 5.2 Transmission Torque Limits: - Take-off power: 440 kw - Max continuous power: 368 kw 6. Fluids (Fuel/Oil/Hydraulic/Additives): 6.1 Fuel: as approved in the Flight Manual 6.2 Oil: as approved in the Flight Manual for engine and gearboxes 6.3 Hydraulic: as approved in the Flight Manual 6.4 Additives: as approved in the Flight Manual 7. Fluid Capacities: 7.1 Fuel cubic tank: 565 l ± 3,13 (149,2 US Gal ± 0,82) usable in flight 555 l (146,6 US Gal) (total tank capacity: 595 l (157,1 US Gal)
TCDS.R.123 Page 10 of 22 7.2 Oil 12 l (3,17 US Gal) quadrilobic tank: 575 l ± 3,13 (151,9 US Gal ± 0,82) usable in flight 573 l (151,3 US Gal) (total tank capacity: 590 l (155,8 US Gal) 8. Airspeed Limits: - For centre of gravity between 2,78 m and 3,08 m: - instruments with metric measures indications: Altitude (m) 0 to 1000 2000 3000 4000 5000 6000 6500 Weight (kg) 2250 2100 1900 1700 1500 220 220 220 220 220 198 206 212 216 218 Vne (km/h) 175 130 184 154 192 165 198 175 202 184 122 145 160 - instruments with imperial measures indications: 110 132 120 Altitude (ft) 0 to 3000 6000 9000 12000 15000 18000 21000 Weight (lb) 4980 4650 4200 3750 3300 108 116 98 103 107 109 112 Vne (kt) 82 90 95 99 102 64 78 86 92 70 80 67 - For centre of gravity between 3,08 m and 3,15 m (single-seat flight): - Instruments with metric measures indications: same limitation as above but Vne limited to 180 km/h up to 3000m and limited to 160 km/h over 3000m. - Instruments with imperial measures indications: same limitation as above but Vne limited to 97 kt up to 10000ft and limited to 85 kt over 10000ft. 9. Rotor Speed Limits: - Max rotor speed: 420 rpm - Min rotor speed: 270 rpm - Max continuous rotor speed: 358 rpm 10. Maximum Operating Altitude and Temperature: 10.1 Altitude : En route: Starting: Restart in flight: 6500m (21300ft) pressure altitude 4000m (13000ft) pressure altitude 5000m (16500ft) pressure altitude 5200m (17000ft) pressure altitude for engine equipped with barostatic controller (modification TURBOMECA ref. TU 81) 10.2 Temperature: - 40 C to + 55 C
TCDS.R.123 Page 11 of 22 11. Operating Limitations: VFR day VFR night when the additional equipment required by operational regulations is installed and serviceable. (For more information refer to approved Flight Manual) 12. Maximum Certified Weights: Take-off and landing: 2250kg (4960,4 lb) 13. Centre of Gravity Range: Longitudinal: Forward limit: 2,78 m Aft limit: 3,08 m Or Forward limit: 3,08 m with the following speed limitation: Aft limit: 3,15 m Maximum translation speed: - For centre of gravity between 2,80 m and 3,08 m: 220 km/h (119 kt) Nota: For altitude over 1500m (4921 ft) and for temperature ISA -20 C Vne must be decreased by 15 km/h (8 kt). - For centre of gravity between 3,08 m and 3,15 m: 180 km/h (97 kt) up to 3000m (9842 ft) 160 km/h (85 kt) over 3000m (9842 ft) Lateral: Left limit: 0,14 m Right limit: 0,12 m 14. Datum: Longitudinal: Lateral: 3 m (9,84 ft) forward of main rotor centreline aircraft symmetry plane 15. Levelling Means: 4 levelling legs on the central structure: - 2 on the front of the aircraft - 2 on the rear of the aircraft 16. Minimum Flight Crew: 1 pilot, at station + 1,385 m 17. Maximum Passenger Seating Capacity: 6 Front seats: 2 passengers at station + 1,385 m Rear seats: 4 passengers at station + 2.195 m 18. Passenger Emergency Exits: Refer to approved Flight Manual 19. Maximum Baggage/Cargo Loads: Refer to approved Flight Manual 20. Rotor Blade and Control Movement: Refer to aircraft Maintenance Manual 21. Auxiliary Power Unit: None
TCDS.R.123 Page 12 of 22 IV. Operating and Service Instructions 1. Rotorcraft Flight Manual, Document No: SA 316C Flight Manual original edition approved by DGAC-F, or later DGAC-F or EASA approved revision. 2. Maintenance Manual, Document No: SA 316C Maintenance Manual 3. Service Letters and Service Bulletins: As published by Aérospatiale or Eurocopter and approved by DGAC-F or EASA 4. Required Equipment: As per compliance with applicable requirements and in accordance with the original Type Design standard; refer to approved Flight Manual. 5. Master Minimum Equipment List: None V. Notes 1. Eligible serial numbers: each ALOUETTE III helicopter complying with SA 316C type 2. The certified optional installations are each approved independently of the basic helicopter and an approved Flight Manual Supplement is associated to each optional installation if necessary. 3. Commercial designation: ALOUETTE III
TCDS.R.123 Page 13 of 22 SA 319B I. General 1. Data Sheet No: EASA.R.123 Corresponding to DGAC-F n 61, issue 7 dated March 1993 2. Type / Variant or Model: (a) Type: SE 316 (b) Variant or Model: SA 319B 3. Airworthiness Category: Small Rotorcraft 4. Type Certificate Holder: Since June 1, 1997 Before June 1, 1997 EUROCOPTER Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE EUROCOPTER FRANCE Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE Between January 1, 1970 and January 1, 1992 AEROSPATIALE 37, Boulevard de Montmorency 75781 PARIS cedex 16 FRANCE Before January 1, 1970 SUD AVIATION 37, Boulevard de Montmorency 75016 PARIS FRANCE 5. Manufacturer: As above 6. National Certification Date: SA 319B May 14, 1971 (DGAC-F National TC N 14) 7. DGAC-F Application Date: N/A 8. DGAC-F Recommendation Date: N/A 9. EASA Certification Date: N/A II. Certification Basis 1. Certification Basis: CAR-6, edition dated December 20, 1956 (including 6-1 to 6-3 amdt) with additional Special Conditions for turbine Helicopter notified at the French DGAC by the government of the United States (FAA letter dated May 03, 1960) 2. Airworthiness Requirements: As defined above 3. Reversions and Exemptions Granted: N/A 4. Equivalent Safety Findings: N/A 5. Special Conditions: Refer to 1 certification basis 6. Environmental Standards including noise: N/A
TCDS.R.123 Page 14 of 22 III. Technical Characteristics and Operational Limitations 1. Type Design Definition: SA 319B: definition of SA 319B is obtained by applying to the SE 3160 modifications according to doc Aérospatiale SA 319 A 04.00.025 2. Description: Small single-engine helicopter. 3. Equipment: As per compliance with applicable airworthiness requirements defined here above and referenced within approved Flight Manual. 4. Dimensions: Fuselage: Length: 10,175 m (33,38 ft) Width: 2,602 m (8,54 ft) Height: 3,000 m (9,84 ft) Main Rotor: 3 blades Diameter: 11,020 m (36,15 ft) Tail Rotor: 3 blades Diameter: 1,920 m (6,30 ft) 5. Engines: 1 Turboméca ASTAZOU XIV B see EASA.E.075 5.1 Installed Engine Limits: - max Rpm: 43000 rpm ± 200 (±1500 rpm during transitory variation allowed) - max power at Take-off: - 640 kw (thermic) on ground - 440 kw (reducer) - max continuous power used: 405 kw (reducer) - max T4 temperature at engine start: 700 C (over temperature during 5 sec allowed: 750 C) - max T4 temperature continuous: - 470 C without modification AB 60/N 40-500 C with modification AB 60/N 40 - max T4 temperature (5 ): 550 C 5.2 Transmission Torque Limits: - Take-off power: 440 kw - Max continuous power: 368 kw 6. Fluids (Fuel/Oil/Hydraulic/Additives): 6.1 Fuel: as approved in the Flight Manual 6.2 Oil: as approved in the Flight Manual for engine and gearboxes 6.3 Hydraulic: as approved in the Flight Manual 6.4 Additives: as approved in the Flight Manual 7. Fluid Capacities: 7.1 Fuel: cubic tank: 565 l ± 3,13 (149,2 US Gal ± 0,82) usable in flight 555 l (146,6 US Gal) (total tank capacity: 595 l (157,1 US Gal)
TCDS.R.123 Page 15 of 22 quadrilobic tank: 575 l ± 3,13 (151,9 US Gal ± 0,82) usable in flight 573 l (151,3 US Gal) (total tank capacity: 590 l (155,8 US Gal) 7.2 Oil: 12 l (3,17 US Gal) 8. Airspeed Limits: - For centre of gravity between 2,78 m and 3,08 m: - instruments with metric measures indications: Altitude (m) 0 to 1000 2000 3000 4000 5000 6000 6500 Weight (kg) 2250 2100 1900 1700 1500 220 220 220 220 220 198 206 212 216 218 Vne (km/h) 175 130 184 154 192 165 198 175 202 184 122 145 160 110 132 120 - instruments with imperial measures indications: Altitude (ft) 0 to 3000 6000 9000 12000 15000 18000 21000 Weight (lb) 4980 4650 4200 3750 3300 108 116 98 103 107 109 112 Vne (kt) 82 90 95 99 102 64 78 86 92 70 80 67 - For centre of gravity between 3,08 m and 3,15 m (single-seat flight): - Instruments with metric measures indications: same limitation as above but Vne limited to 180 km/h up to 3000m and limited to 160 km/h over 3000m. - Instruments with imperial measures indications: same limitation as above but Vne limited to 97 kt up to 10000ft and limited to 85 kt over 10000ft. 9. Rotor Speed Limits: - Max rotor speed: 420 rpm - Min rotor speed: 270 rpm - Max continuous rotor speed: 358 rpm 10. Maximum Operating Altitude and Temperature: 10.1 Altitude: Flight: 6500m (21300 ft) Start: 4000m (13000 ft) In flight restart: 5000m (16500 ft) 10.2 Temperature: - 40 C to + 55 C
TCDS.R.123 Page 16 of 22 11. Operating Limitations: VFR day VFR night when the additional equipment required by operational regulations is installed and serviceable. (For more information refer to approved Flight Manual) 12. Maximum Certified Weights: Take-off and landing: 2250kg (4960,4 lb) 13. Centre of Gravity Range: Longitudinal: Forward limit: 2,78 m Aft limit: 3,08 m Or Forward limit: 3,08 m with the following speed limitation: Aft limit: 3,15 m Maximum translation speed: - For centre of gravity between 2,78 m and 3,08 m: 220 km/h ( kt) Nota: For altitude over 1500m (4921 ft) and for temperature ISA -20 C Vne must be decreased by 15 km/h (8 kt). - For centre of gravity between 3,08 m and 3,15 m: 180 km/h (97 kt) up to 3000m (9842 ft) 160 km/h (85 kt) over 3000m (9842 ft) Lateral: Left limit: 0,14 m Right limit: 0,12 m 14. Datum: Longitudinal: Lateral: 3 m (9,84 ft) forward of main rotor centreline aircraft symmetry plane 15. Levelling Means: 4 levelling legs on the central structure: - 2 on the front of the aircraft - 2 on the rear of the aircraft 16. Minimum Flight Crew: 1 pilot, at station + 1,385 m 17. Maximum Passenger Seating Capacity: 6 Front seats: 2 passengers, at station + 1,385 m Rear seats: 4 passengers, at station + 2,195 m 18. Passenger Emergency Exits: Refer to approved Flight Manual 19. Maximum Baggage/Cargo Loads: Refer to approved Flight Manual 20. Rotor Blade and Control Movement: Refer to aircraft Maintenance Manual 21. Auxiliary Power Unit: None
TCDS.R.123 Page 17 of 22 IV. Operating and Service Instructions 1. Rotorcraft Flight Manual, Document No: SA 319B Flight Manual original edition approved by DGAC-F, or later DGAC-F or EASA approved revision. 2. Maintenance Manual, Document No: SE 319B Maintenance Manual 3. Service Letters and Service Bulletins: As published by Aérospatiale or Eurocopter and approved by DGAC-F or EASA 4. Required Equipment: As per compliance with applicable requirements and in accordance with the original Type Design standard; refer to approved Flight Manual. 5. Master Minimum Equipment List: None V. Notes 1. Eligible serial numbers: each ALOUETTE III helicopter complying with SA 319B type 2. The certified optional installations are each approved independently of the basic helicopter and an approved Flight Manual Supplement is associated to each optional installation if necessary. 3. Commercial designation: ALOUETTE III
TCDS.R.123 Page 18 of 22 SA 315B I. General 1. Data Sheet No: EASA.R.123 Corresponding to DGAC-F n 61, issue 7 dated March 1993 2. Type / Variant or Model: (a) Type: SA 315B 3. Airworthiness Category: Small Rotorcraft 4. Type Certificate Holder: Since June 1, 1997 Before June 1, 1997 EUROCOPTER Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE EUROCOPTER FRANCE Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE Between January 1, 1970 and January 1, 1992 AEROSPATIALE 37, Boulevard de Montmorency 75781 PARIS cedex 16 FRANCE Before January 1, 1970 SUD AVIATION 37, Boulevard de Montmorency 75016 PARIS FRANCE 5. Manufacturer: As above 6. National Certification Date: SA 315B September 29, 1970 (DGAC-F National TC N 14) 7. DGAC-F Application Date: As above 8. DGAC-F Recommendation Date: N/A 9. EASA Certification Date: N/A II. Certification Basis 1. Certification Basis: CAR-6, edition dated December 20, 1956 (including 6-1 to 6-3 amdt) with additional Special Conditions for turbine Helicopter notified at the French DGAC by the government of the United States (FAA letter dated May 03, 1960) 2. Airworthiness Requirements: As defined above 3. Reversions and Exemptions Granted: N/A 4. Equivalent Safety Findings: N/A 5. Special Conditions: Refer to 1 certification basis 6. Environmental Standards including noise: N/A
TCDS.R.123 Page 19 of 22 III. Technical Characteristics and Operational Limitations 1. Type Design Definition: SA 315B SA 315B basic SA 315B definition according to drawing Aérospatiale 315 A.00.10 000. could also be obtained from Alouette II/Alouette Astazou helicopter by applying drawing Aérospatiale 315 A.00.02 000.1. Nota: Alouette III obtained from Alouette II are deemed approved by EASA if this transformation was done before 07 March 2007 when the Alouette II was officially declared to satisfy the definition of the Annex II of Basic Regulation EC 1592/2002. 2. Description: Small single-engine helicopter. 3. Equipment: As per compliance with applicable airworthiness requirements defined here above and referenced within approved Flight Manual. 4. Dimensions: Fuselage: Length: 10,236 m (33,58 ft) Width: 2,380 m (7,80 ft) Height: 3,090 m (10,14 ft) Main Rotor: 3 blades Diameter: 11,020 m (36,15 ft) Tail Rotor: 3 blades Diameter: 1,912 m (6,27 ft) 5. Engines: 1 Turboméca ARTOUSTE III B or III B1 see DGAC-F engine TC M12 5.1 Installed Engine Limits: - max Rpm: 33500 rpm ± 200 (±1000 rpm during transitory variation allowed) - max power at Take-off: - 640 kw (thermic) on ground - 420 kw (reducer) with ARTOUSTE III B - 440 kw (reducer) with ARTOUSTE III B1 - max continuous power used: 405 kw (reducer) - max T4 temperature at engine start: 630 C - max T4 temperature continuous: 500 C - max T4 temperature (5 ): 550 C 5.2 Transmission Torque Limits: - Take-off power: 440 kw - Max continuous power: 368 kw 6. Fluids (Fuel/Oil/Hydraulic/Additives): 6.1 Fuel: as approved in the Flight Manual 6.2 Oil: as approved in the Flight Manual for engine and gearboxes 6.3 Hydraulic: as approved in the Flight Manual 6.4 Additives: as approved in the Flight Manual 7. Fluid Capacities: 7.1 Fuel: cubic tank: 565 l ± 3,13 (149,2 US Gal ± 0,82)
TCDS.R.123 Page 20 of 22 usable in flight 555 l (146,6 US Gal) (total tank capacity: 595 l (157,1 US Gal) quadrilobic tank: 575 l ± 3,13 (151,9 US Gal ± 0,82) usable in flight 573 l (151,3 US Gal) (total tank capacity: 590 l (155,8 US Gal) 7.2 Oil: engine: 10 l (2,64 US Gal) MGB: 6 l (1,58 US Gal) RGB: 0,5 l 8. Airspeed Limits: - For centre of gravity between 2,76 m and 3,00 m: - instruments with metric measures indications: Altitude (m) 0 to 1000 2000 3000 4000 5000 6000 7000 Weight (kg) 1950 1750 1600 1400 1200 210 210 210 210 210 205 208 210 210 210 Vne (km/h) 188 156 192 167 197 177 204 188 210 200 106 135 152 167 182 93 120 140 160 88 110 130 - instruments with imperial measures indications: Altitude (ft) 0 to 3000 6000 9000 12000 15000 18000 21000 23000 Weight (lb) 4300 3850 3500 3000 2500 104 106 110 Vne (kt) 91 95 102 107 112 72 79 89 97 104 58 75 84 95 38 59 70 84 47 61 76 - For centre of gravity between 3,00 m and 3,15 m (single-seat flight): - Instruments with metric measures indications: same limitation as above but Vne limited to 200 km/h. - Instruments with imperial measures indications: same limitation as above but Vne limited to 108 kt. 9. Rotor Speed Limits: - Max rotor speed: 420 rpm - Min rotor speed: 270 rpm - Max continuous rotor speed: 353 rpm 10. Maximum Operating Altitude and Temperature: 10.1 Altitude: Flight: 7000m (23000 ft) Start: 5800m (19000 ft) In flight restart: 5800m (19000 ft)
TCDS.R.123 Page 21 of 22 10.2 Temperature: - 40 C to + 55 C 11. Operating Limitations: VFR day VFR night when the additional equipment required by operational regulations is installed and serviceable. (For more information refer to approved Flight Manual) 12. Maximum Certified Weights: Take-off and landing (with non releasable loads): 1950kg (4299 lb) with gear 315 A 46.10.000. Take-off and landing (with releasable loads): 2300kg (5070,6 lb) Max sling load: 1000kg (2204,6 lb) 13. Centre of Gravity Range: Longitudinal: Forward limit: 2,76 m Aft limit: 3,00 m Or Forward limit: 3,00 m with the following speed limitation and weight limited to 1750 kg (3858 lb): Aft limit: 3,15 m Maximum translation speed: - For centre of gravity between 2,76 m and 3,00 m: 210 km/h ( kt) - For centre of gravity between 3,00 m and 3,15 m: 200 km/h (108 kt) Lateral: Left limit: 0,135 m Right limit: 0,043 m 14. Datum: Longitudinal: Lateral: 3 m (9,84 ft) forward of main rotor centreline aircraft symmetry plane 15. Levelling Means: 4 levelling legs on the central structure: - 2 on the front of the aircraft - 2 on the rear of the aircraft 16. Minimum Flight Crew: 1 pilot, at station + 1,34 m 17. Maximum Passenger Seating Capacity: 4 Front seat: 1 passenger, at station +1,34 m Rear seats: 3 passengers, at station +2,1 m 18. Passenger Emergency Exits: Refer to approved Flight Manual 19. Maximum Baggage/Cargo Loads: Configuration Baggage/Cargo location Max load Station 5 passengers 80 kg each 1 pilot + 1 passenger on front seats Under the rear bench 100 kg (220,4 lb) + 2,2 m Behind the front seats with the rear bench folded up 230 kg (507 lb) + 1.9 m 20. Rotor Blade and Control Movement: Refer to aircraft Maintenance Manual
TCDS.R.123 Page 22 of 22 21. Auxiliary Power Unit: None IV. Operating and Service Instructions 1. Rotorcraft Flight Manual, Document No: SA 315B Flight Manual original edition approved by DGAC-F, or later DGAC-F or EASA approved revision. 2. Maintenance Manual, Document No: SE 315B Maintenance Manual 3. Service Letters and Service Bulletins: As published by Aérospatiale or Eurocopter and approved by DGAC-F or EASA 4. Required Equipment: As per compliance with applicable requirements and in accordance with the original Type Design standard; refer to approved Flight Manual. 5. Master Minimum Equipment List: None V. Notes 1. Eligible serial numbers: each helicopter complying with SA 315B type 2. The certified optional installations are each approved independently of the basic helicopter and an approved Flight Manual Supplement is associated to each optional installation if necessary. 3. Commercial designation: ALOUETTE III LAMA END