# TCDS H10EU: Airbus Helicopters

- Type: Type certificate data sheet
- Status: Current
- Holder: Airbus Helicopters
- Revision: 22
- Revised: July 9, 2026
- Product: Aircraft, Rotorcraft
- Certification basis: Part 29, Part 21
- Registered aircraft: 43, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/d1/00/d100f7305ca683055c6c9a2005c0b7c98446fac1b0fc3e6023ec4fd9a85ba516
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID113683823720260710162157.0001
- Page: https://openairdocs.org/tcds/H10EU

## Models (10)

As the data sheet lists them.

- 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

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
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, 
Code B,             approved July 18, 2000, for Model EC 155 B, or later approved revisions. 
DGAC-approved Helicopter Flight Manual, through Normal Revision RN3, Code B, 
approved  May 5, 2003, for Model EC 155 B1, or later approved revisions. 
 
NOTES. 
NOTE 1. Current weight and balance report including loading instructions and list of equipment included in the 
certificated empty weight, must be provided for each helicopter at the time of original certification. The 
certification empty weight and corresponding center of gravity location must include unusable fuel of 
3.5 lb., at 147.6 in., for the SA 365 C series; 23.1 lb., at 151.6 in., for the SA 365 N; 35.2 lb., at 151.6 
in.,       for the SA 366 G1; 51.8 lb., at 151.6 in., for the SA 365 N1, AS 365 N2, and AS 365 N3. 
 
In order to obtain the most consistent weight and balance results, all helicopters should be weighed on  
jackpoints rather than on wheels and floats.  When changes are made to the helicopter which affect the  
weight and balance, refer to the Flight Manual Weight and Balance Appendix for instructions. 
 
NOTE 2. Information essential to the proper maintenance of the helicopter is contained in the Manufacturer’s 
SA 365 C, C1, C2, N, N1, AS 365 N2, SA 366 G1, AS 365 N3, EC 155 B, and EC 155 B1 Maintenance 
Manual provided  with each helicopter. 
 
NOTE 3. Life limited components and associated retirement times are presented in: 
 
1. SA 365 C series Master Servicing Recommendations, Appendix 5.99 and titled “Airworthiness      
Limitations”. 
2. SA 365 N, N1, AS 365 N2, and AS 365 N3 Master Servicing Recommendations, Appendix  
5.99 and titled “Airworthiness Limitations”. 
3. SA 366 G1 Master Servicing Recommendations, Appendix 5.99 and titled “Airworthiness 
Limitations”. 
4.     EC 155 B Master Servicing Manual, Chapter 4 titled “Airworthiness Limitations”. 
5.     EC 155 B1 Master Servicing Manual, Chapter 4 titled “Airworthiness Limitations”. 
 
All parts and components listed there must be replaced in accordance therewith.

Page 16 of 16 H10EU  
NOTE 4. All placards indicated in the Rotorcraft Flight Manual must be installed in the appropriate location. 
NOTE 5. 1.       The Model SA 365 C may be converted to the Model SA 365 C1 by compliance with 
               Aerospatiale Service Bulletin No. 01.03 dated March 26, 1979. 
       2.       The Models SA 365 C or SA 365 C1 may be converted to the Model SA 365 C2 by compliance 
                                               with Aerospatiale Service Bulletin No. 01.07 dated June 5, 1990. 
3.       Intermix of engine models is not permitted. 
 
NOTE 6. Models SA 365 C or SA 365 C1 helicopters are eligible for operation at the higher limits when: 
 
 1. Aerospatiale modification No. AMS.365A.07.1665 is incorporated. 
2. 
 
3. 
The torquemeter indicator changes described in Aerospatiale Service Bulletin No. 01.06, 
dated January 9, 1980, or later dated revision are accomplished; and 
The DGAC approved Flight Manual revision specified by Service Bulletin 01.06 are 
  included in the Rotorcraft Flight Manual. 
NOTE 7. 1. 
 
2. 
Hover Pressure Refueling system is not approved for installation in Model SA 366 G1 or  
any other model under this type certificate (H10EU) 
Fuel jettison system is approved for Model SA 366 G1 only. 
 
NOTE 8. Model SA 366 G1 operation is restricted to day, VFR only. 
 
NOTE 9. For Model SA 366 G1 only: The limits shown are installed limits.  For computation purposes 100 
percent engine output shaft torque is 643 ft.-lb. and, 100 percent engine output shaft (N2) speed is 
6000 rpm. Also 100% Gas Generator speed is 47,870 rpm. 
 
NOTE 10. For Model SA 366 G1: 
 
1.  Engines - 2 installed Lycoming Model LTS-101-750B-2 with plenum air intake. 
 
2.  Helicopter Modifications - 
 The Aerospatiale modifications defined in Aerospatiale document No. 366A.04.3237     
 must be incorporated. 
 
3.  Flight Manual - 
 The DGAC approved SA 366 G1 Helicopter Flight Manual, Code B, Normal Revision,     
                      approved July 20, 1983, or later approved revision, is required. 
 
NOTE 11. The Models AS 365 N3, EC 155 B, and EC 155 B1 employ electronic engine controls that are recognized to 
be more susceptible to Electromagnetic Interference (EMI). EMI may be the result of radiated or conducted 
interference. Modifications that add or change systems that have a potential for EMI must either be qualified 
to an FAA acceptable standard or tested at the time of installation for interference to the engine controls. 
This type of testing must employ the particular engine control’s diagnostic techniques and external 
diagnostic techniques specified by the engine and helicopter manufacturers. This testing must be 
accomplished in accordance with an FAA approved test plan. 
 
NOTE 12. Model EC 155 B S/Ns 6544-6547, 6557-6559, 6562-6563, 6569, 6575-6577, 6580-6581, and 6583 are 
restricted to day/night VFR operation in the United States unless Mod 07-39B96, Mod 07-25C13, and Mod 
OP-26B17 are incorporated. 
 
NOTE 13.      Effective January 1, 2014, Eurocopter France name was changed to Airbus Helicopters. 
 
 
.....END.....
```

## ADs (145, 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 2026-16-04](https://openairdocs.org/ad/2026-16-04): Time Limits/Maintenance Checks · Airbus Helicopters EC 155 B and EC 155 B1. Effective Sep 17, 2026
- [AD 2025-24-01](https://openairdocs.org/ad/2025-24-01): Passenger Compartment Windows, Door Windows · Airbus Helicopters EC155B1 and EC 155B. Effective Jan 12, 2026
- [AD 2025-14-07](https://openairdocs.org/ad/2025-14-07): Fire Detection System · Airbus Helicopters AS-365N3, EC 155B and EC155B1. Effective Aug 26, 2025
- [AD 2025-13-09](https://openairdocs.org/ad/2025-13-09): Main rotor control · Airbus Helicopters AS-365N2, AS-365N3, EC 155B and 3 more. Effective Aug 14, 2025
- [AD 2025-04-09](https://openairdocs.org/ad/2025-04-09): Bulkhead/Firewall · Airbus Helicopters EC 155B, EC155B1, SA-365N and 3 more. Effective Apr 11, 2025
- [AD 2025-03-02](https://openairdocs.org/ad/2025-03-02): Flight compartment equipment · Airbus Helicopters AS332C, AS332C1, AS332L and 15 more. Effective Mar 7, 2025
- [AD 2025-03-04](https://openairdocs.org/ad/2025-03-04): Cabin Equipment/Furnishings · Airbus Helicopters AS332L, AS332L1, AS-365N3 and 4 more. Effective Feb 19, 2025
- [AD 2024-10-10](https://openairdocs.org/ad/2024-10-10): Tail Rotor Control System · Airbus Helicopters SA-365N, SA-365N1, AS-365N2 and 1 more. Effective Jul 23, 2024
- [AD 2023-22-14](https://openairdocs.org/ad/2023-22-14): Tail rotor gearbox · Airbus Helicopters SA-365C1, SA-365C2 and SA-365N. Effective Dec 26, 2023
- [AD 2023-14-07](https://openairdocs.org/ad/2023-14-07): Main rotor gearbox · Airbus Helicopters EC155B1. Effective Sep 7, 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 2022-22-02](https://openairdocs.org/ad/2022-22-02): Placards and Markings, Passenger/Crew Doors · Airbus Helicopters SA-365N, SA-365N1, AS-365N2 and 3 more. Effective Dec 21, 2022
- [AD 2022-13-14](https://openairdocs.org/ad/2022-13-14): Tail Rotor Drive System · Airbus Helicopters AS-365N2, AS-365N3, EC 155B and 2 more. Effective Aug 15, 2022
- [AD 2022-11-18](https://openairdocs.org/ad/2022-11-18): Engine Cowling System · Airbus Helicopters AS355E, AS355F, AS355F1 and 7 more. Effective Jul 13, 2022
- [AD 2022-10-09](https://openairdocs.org/ad/2022-10-09): Main Rotor Gearbox · Airbus Helicopters SA-365C1 and SA-365C2. Effective Jun 16, 2022
- [AD 2022-09-04](https://openairdocs.org/ad/2022-09-04): Tail Rotor Drive System · Airbus Helicopters SA-365N1, AS-365N2, AS-365N3 and 3 more. Effective May 31, 2022
- [AD 2022-08-02](https://openairdocs.org/ad/2022-08-02): Engine Controls · Airbus Helicopters EC 155B and EC155B1. Effective May 17, 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 2022-01-01](https://openairdocs.org/ad/2022-01-01): Main Rotor System · Airbus Helicopters AS350B, AS350BA, AS350B1 and 17 more. Effective Mar 7, 2022
- [AD 2022-01-03](https://openairdocs.org/ad/2022-01-03): Fire Bottle, Portable · Airbus Helicopters AS332C, AS332C1, AS332L and 35 more. Effective Mar 7, 2022
- [AD 2021-26-18](https://openairdocs.org/ad/2021-26-18): Tail Rotor Drive System · Airbus Helicopters AS-365N2, AS-365N3, SA-365N1 and 5 more. Effective Feb 9, 2022
- [AD 2021-22-16](https://openairdocs.org/ad/2021-22-16): Main Rotor Drive System · Airbus Helicopters EC155B1 and EC 155B. Effective Jan 3, 2022
- [AD 2021-17-17](https://openairdocs.org/ad/2021-17-17): Cabin Equipment/Furnishings · Airbus Helicopters EC135P3, EC135T3, MBB-BK 117 C-2 and 32 more. Effective Nov 22, 2021
- [AD 2021-22-07](https://openairdocs.org/ad/2021-22-07): Fire Bottle, Portable · Airbus A319-111, A319-112, A319-113 and 127 more. Effective Nov 18, 2021
- [AD 2021-18-06](https://openairdocs.org/ad/2021-18-06): Engine Cowling System · Airbus Helicopters AS-365N2, AS-365N3, EC 155B and 3 more. Effective Sep 10, 2021
- [AD 2021-11-10](https://openairdocs.org/ad/2021-11-10): Life Raft · Airbus Helicopters AS-365N2, AS-365N3, SA-365N and 1 more. Effective Aug 27, 2021
- [AD 2021-14-16](https://openairdocs.org/ad/2021-14-16): Fuselage Main, Frame · Airbus Helicopters AS-365N2, AS-365N3, SA-365N and 2 more. Effective Aug 24, 2021
- [AD 2021-13-19](https://openairdocs.org/ad/2021-13-19): Fuselage Structure · Airbus Helicopters AS-365N2, AS-365N3, SA-365N and 1 more. Effective Aug 17, 2021
- [AD 2021-12-05](https://openairdocs.org/ad/2021-12-05): Passenger/Crew Doors · Airbus Helicopters EC155B1. Effective Jul 20, 2021
- [AD 2021-12-06](https://openairdocs.org/ad/2021-12-06): Main Rotor Drive System · Airbus Helicopters AS-365N2, AS-365N3, SA-365N and 1 more. Effective Jul 20, 2021
- [AD 2021-07-07](https://openairdocs.org/ad/2021-07-07): Rotorcraft flight control · Airbus Helicopters EC 155B and EC155B1. Effective May 10, 2021
- [AD 2021-05-06](https://openairdocs.org/ad/2021-05-06): Window/Windshield System · Airbus Helicopters AS332C, AS332C1, AS332L and 6 more. Effective Apr 19, 2021
- [AD 2021-02-08](https://openairdocs.org/ad/2021-02-08): Fuselage Structure · Airbus Helicopters AS-365N2, AS-365N3, EC 155B and 4 more. Effective Apr 15, 2021
- [AD 2021-02-09](https://openairdocs.org/ad/2021-02-09): Main Rotor Gearbox · Airbus Helicopters EC 155B and EC155B1. Effective Apr 15, 2021
- [AD 2021-02-01](https://openairdocs.org/ad/2021-02-01): Placards and markings · Airbus Helicopters AS-365N2, AS-365N3, AS332C and 7 more. Effective Apr 6, 2021
- [AD 2021-03-06](https://openairdocs.org/ad/2021-03-06): Main Rotor Gearbox · Airbus Helicopters AS-365N2, AS-365N3, EC 155B and 3 more. Effective Apr 1, 2021
- [AD 2020-21-15](https://openairdocs.org/ad/2020-21-15): Tail Rotor Gearbox · Airbus Helicopters AS-365N2, AS-365N3, EC 155B and 2 more. Effective Dec 7, 2020
- [AD 2020-20-14](https://openairdocs.org/ad/2020-20-14): Rotorcraft Servo System · Airbus Helicopters AS-365N2, AS-365N3, AS355F and 11 more. Effective Oct 23, 2020
- [AD 2020-15-01](https://openairdocs.org/ad/2020-15-01): Attitude and Direction Data System · Airbus Helicopters EC 155B and EC155B1. Effective Aug 17, 2020
- [AD 2020-10-02](https://openairdocs.org/ad/2020-10-02): Main Rotor System · Airbus Helicopters AS-365N2, AS-365N3, SA-365C and 5 more. Effective Jun 15, 2020
- [AD 2018-18-11](https://openairdocs.org/ad/2018-18-11): Lights · Airbus Helicopters AS-365N2 and AS-365N3. Effective Oct 18, 2018
- [AD 2018-11-03](https://openairdocs.org/ad/2018-11-03): Main Rotor Head · Airbus Helicopters SA-365C, SA-365C1 and SA-365C2. Effective Jun 18, 2018
- [AD 2016-13-07](https://openairdocs.org/ad/2016-13-07): Placards and Markings · Airbus Helicopters AS-365N3. Effective Aug 2, 2016
- [AD 2016-09-09](https://openairdocs.org/ad/2016-09-09): Fuselage Main, Frame · Airbus Helicopters AS-365N2, AS-365N3, SA-365N and 2 more. Effective Jun 10, 2016
- [AD 2016-07-26](https://openairdocs.org/ad/2016-07-26): Horizontal Stabilizer Structure · Airbus Helicopters AS-365N2, AS-365N3, SA-365N and 1 more. Effective May 16, 2016
- [AD 2016-05-10](https://openairdocs.org/ad/2016-05-10): Life Raft · Airbus Helicopters AS-365N3, EC 155B and EC155B1. Effective Mar 28, 2016
- [AD 2015-11-06](https://openairdocs.org/ad/2015-11-06): Main Rotor Control · Airbus Helicopters AS-365N2, AS-365N3, EC 155B and 4 more. Effective Jul 13, 2015
- [AD 2015-10-05](https://openairdocs.org/ad/2015-10-05): Equipment/Furnishing · Airbus Helicopters AS-365N3, EC 155B and EC155B1. Effective Jun 5, 2015
- [AD 2014-26-02](https://openairdocs.org/ad/2014-26-02): Autopilot System · Airbus Helicopters AS-365N3 and EC155B1. Effective Jan 30, 2015

All 145: https://openairdocs.org/tcds/H10EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Eurocopter AS365N3](https://openairdocs.org/model/eurocopter-as365n3): 11 aircraft (registry code 8680903)
- [Eurocopter EC 155 B1](https://openairdocs.org/model/eurocopter-ec-155-b1): 9 aircraft (registry code 8680991)
- [Aerospatiale AS 365 N2 DAUPHIN](https://openairdocs.org/model/aerospatiale-as-365-n2-dauphin): 5 aircraft (registry code 8680815)
- [Eurocopter EC 155B](https://openairdocs.org/model/eurocopter-ec-155b): 4 aircraft (registry code 8681000)
- [Airbus Helicopters EC 155B1](https://openairdocs.org/model/airbus-helicopters-ec-155b1): 3 aircraft (registry code 1145101)
- [Eurocopter AS 365 N2 DAUPHIN](https://openairdocs.org/model/eurocopter-as-365-n2-dauphin): 3 aircraft (registry code 8680952)
- [Eurocopter France AS-365N2](https://openairdocs.org/model/eurocopter-france-as-365n2): 3 aircraft (registry code 8680983)
- [Aerospatiale AS 365 N2](https://openairdocs.org/model/aerospatiale-as-365-n2): 1 aircraft (registry code 8680798)
- [Aerospatiale SA365N-1 DAUPHIN](https://openairdocs.org/model/aerospatiale-sa365n-1-dauphin): 1 aircraft (registry code 8680668)
- [Aerospatiale SA365N1](https://openairdocs.org/model/aerospatiale-sa365n1): 1 aircraft (registry code 8680603)
- [Eurocopter AS365N1](https://openairdocs.org/model/eurocopter-as365n1): 1 aircraft (registry code 868095A)
- [Eurocopter AS365N2](https://openairdocs.org/model/eurocopter-as365n2): 1 aircraft (registry code 868095C)
- [Aerospatiale AS 366G DAUPHIB](https://openairdocs.org/model/aerospatiale-as-366g-dauphib): 0 aircraft (registry code 8680816)
- [Aerospatiale AS365](https://openairdocs.org/model/aerospatiale-as365): 0 aircraft (registry code 8680826)
- [Aerospatiale SA-365-C1](https://openairdocs.org/model/aerospatiale-sa-365-c1): 0 aircraft (registry code 8680666)
- [Aerospatiale SA-365-C2](https://openairdocs.org/model/aerospatiale-sa-365-c2): 0 aircraft (registry code 8680670)
- [Aerospatiale SA-365C "DAUPHIN"](https://openairdocs.org/model/aerospatiale-sa-365c-dauphin): 0 aircraft (registry code 8680667)
- [Aerospatiale SA-366-G1](https://openairdocs.org/model/aerospatiale-sa-366-g1): 0 aircraft (registry code 8680820)
- [Aerospatiale SA365N](https://openairdocs.org/model/aerospatiale-sa365n): 0 aircraft (registry code 8680669)
- [Aerospatiale SA365N-1 ECUREIL](https://openairdocs.org/model/aerospatiale-sa365n-1-ecureil): 0 aircraft (registry code 8680818)
- [Eurocopter DAUPHIN AS 365 N3](https://openairdocs.org/model/eurocopter-dauphin-as-365-n3): 0 aircraft (registry code 8680904)
- [Eurocopter SA365N](https://openairdocs.org/model/eurocopter-sa365n): 0 aircraft (registry code 868081A)

## STCs approved under this data sheet (171, first 50)

- [STC SR12205SE](https://openairdocs.org/stc/SR12205SE): Installation of Onboard Systems International Cargo Hook Kit. Onboard Systems International 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 SR04606NY](https://openairdocs.org/stc/SR04606NY): Installation of Garmin Helicopter Terrain Awareness Warning System (HTAWS). Maxcraft Avionics Ltd.
- [STC SR01949NY-D](https://openairdocs.org/stc/SR01949NY-D): Installation of a Honeywell Chadwick Model 15175 VXP System. Diagnostic Solution International LLC
- [STC SR09498RC-D](https://openairdocs.org/stc/SR09498RC-D): Activation of Eurocopter France Provisions of GPS with WAAS Vertical Guidance. Airbus Helicopters Inc.
- [STC SR00925DE](https://openairdocs.org/stc/SR00925DE): Installation of Garmin GTX 335/335R and GTX345/345R transponders to provide ADS-B Out and In functionality. Peregrine
- [STC SH2216NM](https://openairdocs.org/stc/SH2216NM): Installation of a Sperry Primus 500 weather radar system.. Honeywell International Inc
- [STC SR04412NY](https://openairdocs.org/stc/SR04412NY): Installation of the Latitude SkyNode S200 Satellite Communication (SATCOM) and Tracker System. Maxcraft Avionics Ltd.
- [STC SR04413NY](https://openairdocs.org/stc/SR04413NY): Installation of the Garmin GTN Navigator System. Maxcraft Avionics Ltd.
- [STC SR04414NY](https://openairdocs.org/stc/SR04414NY): Installation of the Garmin GTX Transponder and GTS Traffic System. Maxcraft Avionics Ltd.
- [STC SH1539NM](https://openairdocs.org/stc/SH1539NM): Installation of an air-conditioning system. Air Comm Corporation
- [STC SH7024SW-D](https://openairdocs.org/stc/SH7024SW-D): Relocation of the aircraft dataplate.. Airbus Helicopters Inc.
- [STC SR09634RC](https://openairdocs.org/stc/SR09634RC): Installation of a Balloon Pump Restraint System (BPRS). JJASPP Engineering Services LLC
- [STC SR04147NY](https://openairdocs.org/stc/SR04147NY): Installation of Concorde (p/n RG-365) Lead Acid battery. DECA Aviation Engineering Limited
- [STC SH7572SW](https://openairdocs.org/stc/SH7572SW): Installation of a liquid oxygen, air vacuum, and electrical EMS systems.. RSG Products
- [STC SH8626SW](https://openairdocs.org/stc/SH8626SW): Installation of a Lucas electric hoist.. RSG Products
- [STC SH921NE](https://openairdocs.org/stc/SH921NE): Installation of an Emergency Medical Services Interior.. RSG Products
- [STC SH7573SW](https://openairdocs.org/stc/SH7573SW): Installation of a secondary stretcher and attendant seat combination.. RSG Products
- [STC SH7574SW](https://openairdocs.org/stc/SH7574SW): Installation of a dual pivoting litter carriage.. RSG Products
- [STC SR04056CH](https://openairdocs.org/stc/SR04056CH): Installation of L-3 Communications Avionics Systems Trilogy  Electronic Standby Instrument (Model ESI-2000). Mayday Avionics Inc
- [STC SP03675AT](https://openairdocs.org/stc/SP03675AT): Installation of a Honeywell Solid State Cockpit Voice Flight Data Recorder (SSCVFDR). B/E Aerospace Inc
- [STC SH922NE](https://openairdocs.org/stc/SH922NE): Installation of an emergency medical services Interior.. Sikorsky Aircraft Corporation
- [STC SH924NE](https://openairdocs.org/stc/SH924NE): Installation of a Bendix/King EFS 50 Electronic Flight Instrumentation System and a Bendix/King KNS 660 Flight Management System.. Sikorsky Aircraft Corporation
- [STC SR00022NY](https://openairdocs.org/stc/SR00022NY): Installation of Medevac (EMS) interior.. Sikorsky Aircraft Corporation
- [STC SR00288NY](https://openairdocs.org/stc/SR00288NY): Remove the right hand floor mounted litter, and install a new right hand floor mounted litter support and a 2 person seat. Sikorsky Aircraft Corporation
- [STC SR00580NY](https://openairdocs.org/stc/SR00580NY): Installation of Medical Interior.. Sikorsky Aircraft Corporation
- [STC SR02586NY-D](https://openairdocs.org/stc/SR02586NY-D): Installation of a Lifeport MedDeck System 360-3650 on a Eurocopter AS365N3. Sikorsky Aircraft Corporation
- [STC SR02587NY-D](https://openairdocs.org/stc/SR02587NY-D): Installation of a Medical Interior. Sikorsky Aircraft Corporation
- [STC SH3529SW](https://openairdocs.org/stc/SH3529SW): Installation of medical attendant seats.. RSG Products Inc
- [STC SH3530SW](https://openairdocs.org/stc/SH3530SW): Installation of dual patient litter.. RSG Products Inc
- [STC SH3531SW](https://openairdocs.org/stc/SH3531SW): Installation of dual oxygen system.. RSG Products Inc
- [STC SH3532SW](https://openairdocs.org/stc/SH3532SW): Installation of dual vacuum system.. RSG Products Inc
- [STC SH3533SW](https://openairdocs.org/stc/SH3533SW): Installation of dual compressed air system.. RSG Products Inc
- [STC SH3534SW](https://openairdocs.org/stc/SH3534SW): Installation of 110V AC Inverter System.. RSG Products Inc
- [STC SH3535SW](https://openairdocs.org/stc/SH3535SW): Installation of Balloon Pump Model 700.. RSG Products Inc
- [STC SH3536SW](https://openairdocs.org/stc/SH3536SW): Installation of transport incubator Model 1100.. RSG Products Inc
- [STC SH5832SW](https://openairdocs.org/stc/SH5832SW): Installation of freon air conditioning system with belt driven compressor. RSG Products Inc
- [STC SR01717SE](https://openairdocs.org/stc/SR01717SE): Manufacture and installation of a Supplemental Lighting System. Aviation Specialties Unlimited Inc.
- [STC SH2989SO](https://openairdocs.org/stc/SH2989SO): Installation of a shock isolation mount kit for the FLIR imager.. Bell Helicopter Textron Inc.
- [STC SR09597RC](https://openairdocs.org/stc/SR09597RC): Installation of a Flight Data System. North Flight Data Systems LLC
- [STC SR01343LA](https://openairdocs.org/stc/SR01343LA): Installation of MASS Systems fire extinguisher cartridges as replacements for W. Kidde Aerospace/L Hotellier/Dexaero fire extinguisher cartridges in fire extinguisher bottles installed in the rotorcraft models noted on the FAA Approved Model List SR01343LA dated June 28, 2002, or later FAA approved revisions.  This cartridge is in accordance with MASS Systems Master Drawing List MDL-861345, Revision N/C, dated May 31, 2002, or later FAA approved revisions.. AMETEK AMERON LLC d/b/a MASS Systems
- [STC SR01344LA](https://openairdocs.org/stc/SR01344LA): Installation of MASS Systems fire extinguisher cartridges as replacements for W. Kidde Aerospace/L Hotellier/Dexaero fire extinguisher cartridges in fire extinguisher bottles installed in the rotorcraft models noted on the FAA Approved Model List SR01344LA dated June 28, 2002, or later FAA approved revisions.  This cartridge is in accordance with MASS Systems Master Drawing List MDL-861355, Revision N/C, dated May 31, 2002, or later FAA approved revisions.. AMETEK AMERON LLC d/b/a MASS Systems
- [STC SR09351RC](https://openairdocs.org/stc/SR09351RC): Installation of Bendix/King EFS 50 Electronic Flight Instrumentation System (EPIS). Texas Aviation Services
- [STC SR00529NY](https://openairdocs.org/stc/SR00529NY): Installation of a three or four place divan and optional single seats. RSG AeroDesign LLC
- [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International Inc.
- [STC SR00530NY](https://openairdocs.org/stc/SR00530NY): Installation of a cocoon wall panel system.. Texas Aviation Services
- [STC SR09407RC](https://openairdocs.org/stc/SR09407RC): Installation of forward and aft facing couch.. Texas Aviation Services
- [STC SH699NE](https://openairdocs.org/stc/SH699NE): Installation of a Avionics Specialties power analyzer and recorder Nos. SL17036 &  SL17070  .. Aerosonic Corporation
- [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International
- [STC SR09282RC-D](https://openairdocs.org/stc/SR09282RC-D): Installation of a Honeywell Enhanced Ground Proximity Warning System.. American Eurocopter Corporation

All 171: https://openairdocs.org/tcds/H10EU/stcs.md

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