european aviation safety agency · 2014. 1. 31. · tcds.r.123 page 1 of 22 issue 02, 07 january...

TCDS.R.123 of 22 Issue 02, 07 January 2014

European Aviation Safety Agency

EASA

TYPE-CERTIFICATE DATA SHEET

SE 3160 SA 316B SA 316C SA 319B SA 315B

Type Certificate Holder: AIRBUS HELICOPTERS

Aéroport International Marseille – Provence

13725 Marignane cedex

France

Manufacturer: AIRBUS HELICOPTERS

Aéroport International Marseille – Provence

13725 Marignane cedex

France

Issue 1: 18 January, 2010 Issue 2: 07 January, 2014 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 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2


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


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 January 7, 2014 AIRBUS HELICOPTERS Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE Between June 1, 1997, and January 7, 2014 EUROCOPTER Aéroport International Marseille - Provence 13725 MARIGNANE cedex – France Between January 1, 1992 and June 1, 1997 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 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: 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 Height: 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

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) Vne (km/h)

2200* 2100 1900 1700 ≤1500

210 210 210 210 210

195 200 207 210 210

172 180 188 195 203

140 160 173 185

115 143 160

105 130

* SA 316 B only

- SE 3160 (for instruments with imperial measures indications):

- SA 3f (- SA 316B (for instruments with imperial measures indication):

Altitude (ft) 0 to 3000 6000 9000 12000 15000 18000 21000

Weight (lb) Vne (kt)

4850 4630 4200 3750 ≤ 3300

113 113 113 113 113

107 109 111 113 113

97 101 104 107 110

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.

Altitude (ft) 0 to 3000 6000 9000 12000 15000 18000 21000


4630 4400 4000 3600 ≤ 3300

113 113 113 113 113

109 110 112 113 113

101 103 106 108 110

85 89 94 99 102

79 86 92

58 72 78

51 62


- Instruments with imperial measures indications: same limitation as above but Vne limited to 103 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: 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 (113 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: 3 m (9,84 ft) forward of main rotor centreline Lateral: 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 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 or Airbus

Helicopters 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


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 January 7, 2014 AIRBUS HELICOPTERS Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE Between June 1, 1997, and January 7, 2014 EUROCOPTER Aéroport International Marseille - Provence 13725 MARIGNANE cedex – France Between January 1, 1992 and June 1, 1997 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


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:





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




- 640 kW (thermic) on ground - 440 kW (reducer)



- Take-off power: 440 kW - Max continuous power: 368 kW





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)


quadrilobic tank: 575 l ± 3,13 (151,9 US Gal ± 0,82) usable in flight 573 l (151,3 US Gal)


7.2 Oil 12 l (3,17 US Gal)

8. Airspeed Limits:


- instruments with metric measures indications:

Altitude (m) 0 to 1000 2000 3000 4000 5000 6000 6500


2250 2100 1900 1700 ≤1500

220 220 220 220 220

198 206 212 216 218

175 184 192 198 202

130 154 165 175 184

122 145 160

110 132

120

- instruments with imperial measures indications:

Altitude (ft) 0 to 3000 6000 9000 12000 15000 18000 21000


4980 4650 4200 3750 ≤ 3300

118 118 118 118 118

108 113 116 118 118

98 103 107 109 112

82 90 95 99 102

64 78 86 92

70 80

67


- 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.




10.1 Altitude : En route: 6500m (21300ft) pressure altitude

Starting: 4000m (13000ft) pressure altitude Restart in flight: 5000m (16500ft) pressure altitude

5200m (17000ft) pressure altitude for engine equipped with barostatic controller (modification TURBOMECA ref. TU 81)


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


- 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)




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 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.



SA 316C Maintenance Manual

3. Service Letters and Service Bulletins: As published by Aérospatiale or Eurocopter or Airbus



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



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 January 7, 2014 AIRBUS HELICOPTERS Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE

Between June 1, 1997, and January 7, 2014 EUROCOPTER Aéroport International Marseille - Provence 13725 MARIGNANE cedex – France Between January 1, 1992 and June 1, 1997 EUROCOPTER FRANCE

Aéroport International Marseille - Provence 13725 MARIGNANE cedex - 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)




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



- 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:










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)


7.2 Oil: 12 l (3,17 US Gal) 8. Airspeed Limits:



Altitude (m) 0 to 1000 2000 3000 4000 5000 6000 6500


2250 2100 1900 1700 ≤1500

220 220 220 220 220

198 206 212 216 218

175 184 192 198 202

130 154 165 175 184

122 145 160

110 132

120


Altitude (ft) 0 to 3000 6000 9000 12000 15000 18000 21000


4980 4650 4200 3750 ≤ 3300

118 118 118 118 118

108 113 116 118 118

98 103 107 109 112

82 90 95 99 102

64 78 86 92

70 80

67


- 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.




10.1 Altitude: Flight: 6500m (21300 ft) Start: 4000m (13000 ft) In flight restart: 5000m (16500 ft)



11. Operating Limitations: VFR day


(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


- For centre of gravity between 2,78 m and 3,08 m: 220 km/h (118 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)




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


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.


SE 319B Maintenance Manual 3. Service Letters and Service Bulletins: As published by Aérospatiale or Eurocopter or Airbus



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



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 January 7, 2014 AIRBUS HELICOPTERS Aéroport International Marseille - Provence 13725 MARIGNANE cedex - FRANCE

Between June 1, 1997, and January 7, 2014 EUROCOPTER Aéroport International Marseille - Provence 13725 MARIGNANE cedex – France Between January 1, 1992 and June 1, 1997 EUROCOPTER FRANCE

Aéroport International Marseille - Provence 13725 MARIGNANE cedex - 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:


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 III. Technical Characteristics and Operational Limitations 1. Type Design Definition:

SA 315B basic SA 315B definition according to drawing Aérospatiale

315 A.00.10 000. SA 315B 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




- 640 kW (thermic) on ground - 420 kW (reducer) with ARTOUSTE III B - 440 kW (reducer) with ARTOUSTE III B1












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)


7.2 Oil: engine: 10 l (2,64 US Gal) MGB: 6 l (1,58 US Gal) RGB: 0,5 l

8. Airspeed Limits:



Altitude (m) 0 to 1000 2000 3000 4000 5000 6000 7000


1950 1750 1600 1400 ≤1200

210 210 210 210 210

205 208 210 210 210

188 192 197 204 210

156 167 177 188 200

106 135 152 167 182

93 120 140 160

88 110 130


Altitude (ft) 0 to 3000 6000 9000 12000 15000 18000 21000 23000


4300 3850 3500 3000 ≤ 2500

113 113 113 113 113

113 113 113 113 113

104 106 110 113 113

91 95 102 107 112

72 79 89 97 104

58 75 84 95

38 59 70 84

47 61 76


- 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.




10.1 Altitude: Flight: 7000m (23000 ft) Start: 5800m (19000 ft) In flight restart: 5800m (19000 ft)



11. Operating Limitations: VFR day


(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 (113 kt) - For centre of gravity between 3,00 m and 3,15 m: 200 km/h (108 kt)




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

Under the rear bench 100 kg (220,4 lb) + 2,2 m

1 pilot + 1 passenger on front seats

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


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 or Airbus



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__________

european aviation safety agency · 2014. 1. 31. · tcds.r.123 page 1 of 22 issue 02, 07 january...

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