# TCDS H11EU: Airbus Helicopters

- Type: Type certificate data sheet
- Status: Current
- Holder: Airbus Helicopters
- Revision: 12
- Revised: February 8, 2022
- Product: Aircraft, Rotorcraft
- Certification basis: Part 21, Part 27
- Registered aircraft: 35, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/83/5e/835e171c005af37651b50a6d30406ae60b6795632cdc9be8d3e7c43b363df365
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/1BB47AEA507869F5862587E9004D046D.0001
- Page: https://openairdocs.org/tcds/H11EU

## Models (6)

As the data sheet lists them.

- AS355NP
- AS355N
- AS355F2
- AS355F1
- AS355E
- AS355F

## What the data sheet says

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

```text
1------+----+---+----+----+----+----+----+-_+----+--_f--------+----+----+-------ll I 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
H11EU 
Revision 12 
Airbus Helicopters 
AS355E 
AS355F 
AS355F1 
AS355F2 
AS355N 
AS355NP 
February 8, 2022 
TYPE CERTIFICATE DATA SHEET No. H11EU 
This Data Sheet which is part of Type Certificate No. H11EU, 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 
Aeroport International Marseille Provence 
13725 - Marignane - Cedex 
France 
TC Holder Record: Eurocopter France changed name to Airbus Helicopters on January 1, 2014. 
I. Model AS355E "TWINSTAR" (Normal Category), November 20, 1981. 
Engine. 2 ALLISON Model 250-C20F 
Installed Engine Limits. 
Torque 
Gas 
Generator 
Speed 
Exhaust 
Gas 
Temp. 
Output 
Shaft 
Speed 
Take-off (5 min) 
Maximum Continuous 
(two engines operative) 
(one engine inoperative) 
380 mN (73%) 
380 mN (73%) 
521 mN (100%) 
53519 rpm 
" 
" 
810ºC 
738ºC 
810ºC 
6196 rpm 
" 
" 
Engine gearbox Torque limit = 384 ft - lb (521 mN) = 100% 
Refer to Flight Manual AS355E for transients. 
Fuel. Refer to Flight Manual AS355E for approved fuels and additive specifications. 
Helicopter Limits. Maximum (one engine inoperative): 
Maximum (two engines operative): 
100% (521 mN) 
73% (380 mN) 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 
Rev. No. 12 6 3 6 4 10 6 10 6 10 10 10 10 10 12 11

500 
2400 
2200 
2100 
2000 
1900 
1850 
1800 
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125 
124.8 
130 
◄ CG (in) 
135 
► 
139.3 
2 of 16 H11EU 
C.G. Range Longitudinal 
Datum. Longitudinal = 133.8 in. forward of main rotor hub center 
Lateral = Vertical plane passing longitudinally through main rotor hub center 
Maximum Weight. 4628 lb (2100 kg) 
Rotor Speed. Power-off 
maximum = 425 rpm 
minimum = 330 rpm 
Power-on 
= 390 
= 375 to 394 
rpm with both engine operating 
rpm with one engine inoperative 
Rotor Speed Warning. Aural at 360 rpm 
Airspeed Limits. Never exceed speed VNE Power-on: 
0 - 73% torque. 150 kts at zero pressure altitude. 
Doors removed, 70 kts at zero pressure altitude. 
73% - 78% torque. 55 kts at all altitudes. 
Never exceed speed VNE Power-off: 
120 kt at zero pressure-altitude 
See Rotorcraft Flight Manual for decrease of these values with altitude and temperature. 
Minimum Crew. 1 pilot at 60.62 in. - Starboard seat 
Maximum Passenger. (5). 4 at 98.42 in. 
1 at 60.62 in. 
Maximum Baggage. Right baggage compartment = 220 lb at 125.98 in 
Left baggage compartment = 264 lb at 125.908 in 
Rear baggage compartment = 176 lb at 181.10 in 
Main cabin (on rear = 682 lb at 88.58 in 
(on LH forward = 330 lb at 61.02 in

3 of 16 H11EU 
Fuel Capacity. 
Front Tank Rear Tank 
Total 88.1 U.S. gallons 106.5 U.S. gallons 
Usable 87.2 U.S. gallons 105.7 U.S. gallons 
C.G. Range 127.55 in 151.55 in 
See NOTE 1 for data on unusable fuel. 
Empty Weight CG Range. None 
Leveling Means. Transmission support platform. 
Oil Capacity. Engine 
MGB 
TGB 
= 2 x 1.5 U.S. gallons at 140.5 in 
= 2.9 U.S. gallons at 145.2 in 
= 0.08 U.S. gallons at 379.5 in 
Rotor Blades and Control For rigging information, refer to the AS 355 Maintenance Manual. 
Movements. 
II. Model AS 355-F "TWINSTAR" (Normal Category), November 20, 1981. 
(Same as model AS355E except for maximum weight and dual hydraulic systems). 
Engine. 2 ALLISON Model 250-C20F. 
Installed Engine Limits. 
Torque 
Gas 
Generator 
Speed 
Exhaust 
Gas 
Temp. 
Output 
Shaft 
Speed 
Take-off (5 min) 
(two engines operative) 
Maximum 
Continuous (one engine operative) 
380 mN (73%) 
380 mN (73%) 
521 mN (100%) 
53519 rpm 
" 
" 
810ºC 
738ºC 
810ºC 
6196 rpm 
" 
" 
Engine gearbox torque limit = 384 ft=lb (521 mN) = 100% 
Refer to Flight Manual AS355F for transients. 
Fuel. Refer to Flight Manual AS355F for approved fuels and additive specification. 
Helicopter Limits. Maximum (one engine inoperative): 100% (521 mN) 
Maximum (two engines operative): 73% (380 mN) 
C.G. Range. Longitudinal

2600 
2500 
2400 
~ ~ 
~ 
2200 
., 
~ ~ 
2000 
1900 ' l ·Y I 
~ 
1800 
I 
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◄ CENTRAGE [m] ► 0 3.5 4 
3.30 3.40 T., 3.50 
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1 LIMITE AVANT 
FORWARD LIMIT 
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4 of 16 H11EU 
Lateral - Right = 3.54 in 
Left = 6.30 in 
Datum. Longitudinal = 133.8 in. forward of main rotor hub center 
Lateral = Vertical plane passing longitudinally through main rotor hub center 
Maximum Weight. 5070 lb (2300 kg) 
Rotor Speed. Power-off 
maximum = 425 rpm 
minimum = 330 rpm 
Power-on 
= 390 
= 375 to 394 
rpm with both engines operating 
rpm with one engine inoperative 
Rotor Speed Warning. Aural at 360 rpm 
Airspeed Limits. Never exceed speed VNE Power-on: 
150 kt at zero pressure altitude. Doors removed; 70 knots at zero pressure altitude. 
Never exceed speed VNE Power-off 
120 kt at zero pressure-altitude 
See Rotorcraft Flight Manual for decrease of these values with altitude and temperature. 
Minimum Crew. 1 pilot at 60.62 in. - Starboard seat 
Maximum Passengers (5). 4 at 98.42 in. 
1 at 60.62 in. 
Maximum Baggage. Right baggage compartment = 220 lb at 125.98 in 
Left baggage compartment = 264 lb at 125.908 in 
Rear baggage compartment = 176 lb at 181.10 in 
Main cabin (on rear = 682 lb at 88.58 in 
(on LH forward = 330 lb at 61.02 in)

5 of 16 H11EU 
Fuel Capacity. 
Front Tank Rear Tank 
Total 88.1 U.S. gallons 106.5 U.S. gallons 
Usable 87.2 U.S. gallons 105.7 U.S. gallons 
C.G. Range 127.55 in 151.55 in 
See NOTE 1 for data on unusable fuel. 
Empty Weight CG Range. None 
Leveling Means. Transmission support platform. 
Oil Capacity. Engine 
MGB 
TGB 
= 2 x 1.5 U.S. gallons at 140.5 in 
= 2.9 U.S. gallons at 145.2 in 
= 0.08 U.S. gallons at 379.5 in 
Rotor Blades and Control For rigging information, refer to the AS 355 Maintenance Manual. 
Movements. 
III. Model AS 355-F1 "TWINSTAR" (Normal Category), April 11, 1984. 
Engine. 2 ALLISON Model 250-C20F 
Installed Engine Limits. 
Torque 
Gas 
Generator 
Speed 
Exhaust 
Gas 
Temp. 
Output 
Shaft 
Speed 
Take-off (5 min) 
Maximum Continuous 
(two engines operative) 
(one engine operative) 
406 mN (78%) 
380 mN (73%) 
521 mN (100%) 
53,519 rpm 
" 
" 
810ºC 
738ºC 
810ºC 
6,196 rpm 
" 
" 
Engine gearbox Torque limit = 384 ft=lb (521 mN) = 100% 
Refer to Flight Manual AS355F1 for transients. 
Fuel. Refer to Flight Manual AS355F1 for approved fuels and additive specifications. 
Helicopter Limits. Maximum (one engine inoperative): 
Maximum (two engines operative): 
100% (521 mN) 
78% (406 mN)

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6 of 16 H11EU 
C.G. Range. Longitudinal 
Lateral - Right = 3.54 in 
- Left = 6.30 in 
Datum. Longitudinal 
Lateral 
= 133.8 in. forward of main rotor hub center 
= Vertical plane passing longitudinally through main rotor hub 
center. 
Maximum Weight. 5291 lb (2400 kg) 
Rotor Speed. Power-off 
maximum = 425 rpm 
minimum = 330 rpm 
Power-on 
= 390 
= 375 to 394 
rpm with both engines operating 
rpm with one engine inoperative 
Rotor Speed Warning. Aural at 360 rpm and 410 rpm. 
Airspeed Limits. Never exceed speed VNE Power-on: 
150 kt at zero pressure altitude. Doors removed; 70 knots at zero pressure altitude. 
Never exceed speed VNE Power-off 
120 kt at zero pressure-altitude 
See Rotorcraft Flight Manual for decrease of these values with altitude 
and temperature. 
Minimum Crew. 1 pilot at 60.62 in. - Starboard seat 
Maximum Passengers Standard(5). 4 at 98.42 in. 
1 at 60.62 in. 
Maximum passengers of 6 is available when the aircraft is equipped with the optional 
two-place seat at 60.62 in. This optional item is to be used in accordance with the 
associated Flight Manual supplement. 
Maximum Baggage. Right baggage compartment = 220 lb at 125.98 in 
Left baggage compartment = 264 lb at 125.908 in 
Rear baggage compartment = 176 lb at 181.10 in 
Main cabin (on rear = 682 lb at 88.58 in 
(on LH forward = 330 lb at 61.02 in

7 of 16 H11EU 
Fuel Capacity. 
Front Tank Rear Tank 
Total 88.1 U.S. gallons 106.5 U.S. gallons 
Usable 87.2 U.S. gallons 105.7 U.S. gallons 
C.G. Range 127.55 in 151.55 in 
See NOTE for data on unusable fuel. 
Empty Weight CG Range. None 
Leveling Means. Transmission support platform 
Oil Capacity. Engine 
MGB 
TGB 
= 2 x 1.5 U.S. gallons at 140.5 in 
= 2.9 U.S. gallons at 145.2 in 
= 0.08 U.S. gallons at 379.5 in 
Rotor Blades and Control For rigging information, refer to the AS 355 Maintenance Manual. 
Movements. 
IV. Model AS355F2 "TWINSTAR" (Normal Category), February 13, 1987. 
(Same as AS355F1 except for maximum weight, external load maximum weight, yaw compensation system, etc.) 
Engine. 2 ALLISON Model 250-C20F 
Installed Engine Limits. 
Torque 
Gas 
Generator 
Speed 
Exhaust 
Gas 
Temp. 
Output 
Shaft 
Speed 
Take-off (5 min) 
Maximum Continuous 
(two engines operative) 
(one engine operative) 
406 mN (78%) 
380 mN (73%) 
521 mN (100%) 
53,519 rpm 
" 
" 
810ºC 
738ºC 
810ºC 
6,196 rpm 
" 
" 
Engine gearbox Torque limit = 384 ft=lb (521 mN) = 100% 
Refer to Flight Manual AS355F2 for transients. 
Fuel. Refer to Flight Manual AS355F2 approved fuels and additive specification. 
Helicopter Limits. Maximum (one engine inoperative): 
Maximum (two engines operative): 
100% (521 mN) 
78% (406 mN)

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8 of 16 H11EU 
C.G. Range. Longitudinal 
Lateral - Right 
- Left 
= 3.54 in 
= 6.30 in 
Datum. Longitudinal 
Lateral 
= 133.8 in. forward of main rotor hub center 
= Vertical plane passing longitudinally through main rotor hub center 
Maximum Weight. 5600 lb (2540 Kg) 
Rotor Speed. Power-off 
maximum = 425 rpm 
minimum = 330 rpm 
Power-on 
= 390 
= 375 to 394 
rpm with both engines operating 
rpm with one engine inoperative 
Rotor Speed Warning. Aural at 360 rpm and 410 rpm. 
Airspeed Limits. Never exceed speed VNE Power-on: 
150 kt zero pressure altitude. Doors open or removed: 70 knots at zero pressure altitude. 
Never exceed speed VNE Power-off 
120 kt at zero pressure-altitude 
See Rotorcraft Flight Manual for decrease of these values with altitude and temperature. 
Minimum Crew. 1 pilot at 60.62 in. - Starboard seat 
Maximum Passengers Standard (5). 4 at 98.42 in. 
1 at 60.62 in. 
Maximum passengers of 6 is available when the aircraft is equipped with the optional 
two-place seat at 60.62 in. This optional item is to be used in accordance with the 
associated Flight Manual supplement. 
Maximum Baggage. Right baggage compartment = 220 lb at 125.98 in 
Left baggage compartment = 264 lb at 125.908 in 
Rear baggage compartment = 176 lb at 181.10 in 
Main cabin (on rear = 682 lb at 88.58 in 
(on LH forward = 330 lb at 61.02 in

9 of 16 H11EU 
Fuel Capacity. 
Front Tank Rear Tank 
Total 88.1 U.S. gallons 106.5 U.S. gallons 
Usable 87.2 U.S. gallons 105.7 U.S. gallons 
C.G. Range 127.55 in 151.55 in 
See NOTE for data on unusable fuel. 
Empty Weight CG Range. None 
Leveling Means. Transmission support platform 
Oil Capacity. Engine 
MGB 
TGB 
= 2 x 1.5 U.S. gallons at 140.5 in 
= 2.9 U.S. gallons at 145.2 in 
= 0.08 U.S. gallons at 379.5 in 
Rotor Blade and Control For rigging information, refer to the AS355 Maintenance Manual. 
Movements. 
V. Model AS355N "Twinstar" (Normal Category), October 15, 1992. 
The major difference between the AS355N and AS355F series is the replacement of the Allison C250 engines with 
Turbomeca Arrius 1 A engines. 
Engine. 2 Turbomeca model Arrius 1 A controlled by a digital electronic control units. 
Installed Engine Limits. 
Torque 
Gas 
Generator 
Speed 
Exhaust 
Gas 
Temp. 
Output 
Shaft 
Speed 
Take-off (5 min) 
Maximum Continuous 
two engines operative 
Maximum continuous 
one engine operative 
30 mn. one engine inoperative 
2 mn. 30s one engine inoperative 
406 mN (78%)* 
380 mN (73%)* 
521 mN (100%)* 
599 mN (115%) * 
683 mN (131%) 
54,685 rpm 
53,285 rpm 
53,285 rpm 
55,300 rpm 
56,140 rpm 
800ºC 
765ºC 
765ºC 
800ºC 
870ºC 
6,256 rpm 
6,256 rpm 
6,256 rpm 
6,256 rpm 
6,256 rpm 
* Torque limits of helicopter main gearbox 
Engine gearbox torque limit = 521 mN (100% torque) 
refer to Flight Manual AS355N for transients. 
Fuel. Refer to Flight Manual AS355N for approved fuels and additive specifications. 
Helicopter Limits. One engine inoperative: 
Maximum continuous torque: 100% (521 mN) 
30 mn. torque: 115% (599mN). 
2mn 30s. torque: 131% (683 mN). 
Two engines operative: 
IAS < 55 Kts.: 78% (406 mN). 
IAS > 55 Kts.: 73% (380 mN).

(m) 
l .11 l.25 3.45 3.§4 
121 3.30 HO l.50 
2600 
Gill 
2508 
" 
/ '-
mm 
5500 
2400 
oil 2180 
g 
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2208 
1§ 8 ~ ~ 
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I 
REARWARD LIMIT ➔ 
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4500 
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1800 
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CENTERING 
10 of 16 H11EU 
C.G. Range. Longitudinal 
Lateral - Right 
- Left 
= 0.09 m (3.54 in) 
= 0.16 m (6.30 in) 
Datum. Longitudinal = 3.40 m (133.8 in. forward of main rotor hub center) 
Lateral = Vertical plane passing longitudinally through main rotor hub center. 
Maximum Weight. 5732 lb (2600 kg) 
Rotor Speed Limitations. Power-on flight 
- two engines in operation: 390 (+ 4, -5) rpm 
For IAS below 55 kt: 390 (+ 10, -5) rpm 
- OEI : 375 to 394 rpm 
Power-off flight 
- max. 425 rpm (aural warning at 410 rpm) 
- min. 330 rpm (aural warning at 360 rpm) 
Airspeed Limits. Never exceed speed VNE Power-on: 
150 kt zero pressure altitude. 
Doors removed: see the flight manual (section 2.1, § 5.2.) 
Never exceed speed VNE Power-off: 
120 kt at zero pressure-altitude. 
See Rotorcraft Flight Manual for decrease of these values with altitude 
and temperature. 
Minimum Crew. 1 pilot at 60.62 in. - Starboard seat. 
Maximum Passenger Standard (5). 
Maximum Baggage. 
4 at 98.42 in. 
1 at 60.62 in. 
Maximum passengers of 6 is available when the aircraft is equipped with the optional 
two-place seat at 60.62 in. This optional item is to be used in accordance with the 
associated Flight Manual supplement. 
Right baggage compartment = 220 lb at 125.98 in 
Left baggage compartment = 264 lb at 125.908 in 
Rear baggage compartment = 176 lb at 181.10 in 
Main cabin (on rear = 682 lb at 88.58 in 
(on LH forward = 330 lb at 61.02 in

11 of 16 H11EU 
Fuel Capacity. 
Front Tank Rear Tank 
Total 88.1 U.S. gallons 106.5 U.S. gallons 
Usable 87.2 U.S. gallons 105.7 U.S. gallons 
C.G. Range 127.55 in 151.55 in 
See NOTE 1 for data on unusable fuel. 
Empty Weight CG Range. None 
Leveling Means. Transmission support platform. 
Oil Capacity. Engine 
MGB 
TGN 
= 2 x 1.5 U.S. gallons at 140.5 in 
= 2.9 U.S. gallons at 145.2 in 
= 0.08 U.S. gallons at 379.5 in 
Rotor Blade and Control For rigging information, refer to the AS 355 Maintenance Manual. 
Movements. 
VI. Model AS355NP "Twinstar" (Normal Category), January 9, 2008. 
The major difference between the AS355NP and AS355N is the replacement of the Turbomeca Arrius 1A engines with 
Turbomeca Arrius 1A1 engines, addition of New engine monitoring system: VEMD (Vehicule and Engine Multifunction 
Display), electric oil cooling fan and upgraded main gear box. 
Engine. 2 Turbomeca model Arrius 1A1 controlled by a digital electronic control units. 
Installed Engine Limits. 
Torque 
Gas 
Generator 
Speed 
Exhaust 
Gas 
Temp. 
Output 
Shaft 
Speed 
Take-off (5 min) 
Maximum Continuous 
two engines operative 
Maximum continuous 
one engine operative 
2 mn. 30s one engine inoperative 
450 mN (86.4%)* 
374 mN (71.8%)* 
599 mN (115%)* 
683 mN (131%) 
54,375 rpm 
53,285 rpm 
55,452 rpm 
56,347 rpm 
773ºC 
749ºC 
812ºC 
885ºC 
6,016 rpm 
6,016 rpm 
6,016 rpm 
6,016 rpm 
* Torque limits of helicopter main gearbox 
Engine gearbox torque limit = 521 mN (100% torque) 
refer to Flight Manual AS355NP for transients. 
Fuel. Refer to Flight Manual AS355NP for approved fuels and additive specifications. 
Helicopter Limits. One engine inoperative: 
Maximum continuous torque: 
2mn 30s. torque: 
115% (599 mN) 
131% (683 mN). 
Two engines operative: 
IAS < 55 Kts.: 
IAS > 55 Kts.: 
86.4% (450 mN). 
71.8% (374 mN).

5732 1 
18 0 0 ::;'t::D;;:::::=:=:::::::;:=::~;:::::;::::::~:::::::::;::::::;;:::=:::;::::::;:::::::::;:::;::::;:::::::=::::::;::::::::::;::;: - 410 0 0 
I I I 
~ 8 130 1~35-~ 
[g!]] 1128 .3 ◄ CG ( in ) ► 135.4 139.3 1 
12 of 16 H11EU 
C.G. Range. Longitudinal 
Lateral - Right 
- Left 
- Left 
= 0.09 m (3.54 in) 
= 0.09 m (3.54 in) 
= 0.16 m (6.30 in) (hoisting operation) 
Datum. Longitudinal = 3.40 m (133.8 in. forward of main rotor hub center) 
Lateral = Vertical plane passing longitudinally through main rotor hub center. 
Maximum Weight. 5732 lb (2600 kg) 
Rotor Speed Limitations. Power-on flight 
- two engines in operation 375-394 rpm 
For IAS below 55 kt: 390 (+ 10, -5) rpm 
- OEI : 375 to 394 rpm 
Power-off flight 
- max. 425 rpm (aural warning at 410 rpm) 
- min. 330 rpm (aural warning at 360 rpm) 
Maximum Rotor Brake Application: 170 rpm 
Airspeed Limits. Never exceed speed VNE Power-on: 
150 kt zero pressure altitude. 
Doors removed: see the flight manual (section 2, § 2.3) 
Never exceed speed VNE Power-off: 
120 kt at zero pressure-altitude. 
See Rotorcraft Flight Manual for decrease of these values with altitude 
and temperature. 
Minimum Crew. 1 pilot at 60.62 in. - Starboard seat. 
Maximum Passenger Standard(5). 4 at 98.42 in. 
1 at 60.62 in.

13 of 16 H11EU 
Maximum passengers of 6 is available when the aircraft is equipped with the optional 
two-place seat at 60.62 in. This optional item is to be used in accordance with the 
associated Flight Manual supplement. 
Maximum Baggage. Right baggage compartment = 220 lb at 125.98 in 
Left baggage compartment = 264 lb at 125.908 in 
Rear baggage compartment = 176 lb at 181.10 in 
Main cabin (on rear = 682 lb at 88.58 in 
(on LH forward = 330 lb at 61.02 in 
Fuel Capacity. 
Front Tank Rear Tank 
Total 88.1 U.S. gallons 106.5 U.S. gallons 
Usable 87.2 U.S. gallons 105.7 U.S. gallons 
C.G. Range 127.55 in 151.55 in 
See NOTE 1 for data on unusable fuel. 
Empty Weight CG Range. None 
Leveling Means. Transmission support platform. 
Oil Capacity. Engine 
MGB 
TGN 
= 2 x 1.5 U.S. gallons at 140.5 in 
= 2.9 U.S. gallons at 145.2 in 
= 0.08 U.S. gallons at 379.5 in 
Rotor Blade and Control 
Movements. 
For rigging information, refer to the AS 355 Maintenance Manual. 
Certification Basis. AS355E 
AS355F, AS355F1, AS355F2 
FAR 21.29 and FAR 27 effective February 1, 1965 plus Amendments 27-1 through 
27-16. 
Type Certificate No. H11EU, issued January 19, 1981. Amended 
November 20, 1981 to add Model AS355F. Amended April 11, 1984 
to add Model AS355F1. Amended February 13, 1987 to add Model 
AS355F2. Date of Application for Type Certificate: January 4, 1979. 
AS 355 N version: 
- The basic certification basis consists of FAR 21.29 and FAR 27 
effective February 1, 1965, including amendments 27.1 through 27.20, plus 
- The following sections of amendment 27.21: 
27.21, 27.45, 27.71, 27.79, 27.143, 27.151, 27.161, 27.173, 27.175, 
27.177, 27.672, 27.673, 27.729, 27.735, 27.779, 27.807, 27.1329, 
27.1413, 27.1519, 27.1525, 27.1555, 27.1585 and 27.1587. 
DGAC special conditions notified in letter DGAC No. 54408 dated October 21, 1988 
are: 
A - Limit Pilot Forces 
B - Engine air intake protection against birds (2 lbs) and hail ingestion 
C - Engine governing system 
The FADEC has been HIRF tested on the Arrius 1A engine with success at 200V/m 
according to Cat Y DO160. 
In this certification basis, the following sections remain at the Amendment preceding the 
Amendment 27.21: 27.141, 27.610, 27.785, 27.1309, 27.1505 and 27.1559.

14 of 16 H11EU 
The French Direction Generale de l’Aviation Civile (DGAC) originally type certificated 
this rotorcraft under its type certificate TC 168. The FAA validated this product under 
U.S. Type Certificate Number H11EU. Effective September 28, 2003, the European 
Aviation Safety Agency (EASA) began oversight of this product on behalf of the DGAC. 
AS 355 NP version: 
- The basic certification basis consists of FAR 21.29 and FAR 27 
effective February 1, 1965, including amendments 27.1 through 27.20, plus 
- The following sections of amendment 27.21: 
27.21, 27.45, 27.71, 27.79, 27.143, 27.151, 27.161, 27.173, 27.175, 
27.177, 27.672, 27.673, 27.729, 27.735, 27.779, 27.807, 27.1329, 
27.1413, 27.1519, 27.1525, 27.1555, 27.1585 and 27.1587. 
- The following section of amendment 27.23: 27.923 
DGAC special conditions notified in letter DGAC No. 54408 dated October 21, 1988 
are: A - Limit Pilot Forces 
B - Engine air intake protection against birds (2 lbs) and hail ingestion 
C - Engine governing system 
The FADEC HIRF approval for the Arrius 1A1 was accomplished by similarity to the 
testing accomplished on the Arrius 1A engine installed on the AS355N helicopter. 
The AS355NP also complies with the following FAR 29 paragraphs: §45(a) and (b)(2) 
Amdnt 24; §49(a) Amdnt 39; §51 Amdnt 39; §53 Amdnt 39; §55 Amdnt 39; 
§59 Amdnt 44; §60 Amdnt 39; §61 Amdnt 39; §62 Amdnt 44; §64 Amdnt 39; 
§65(a) Amdnt 39; §67(a) Amdnt 44; §75 Amdnt 39; §77 Amdnt 44; §79 Amdnt 
39; §81 Amdnt 44; §85 Amdnt 44; §87(a) Amdnt 39; §861(a) Amdnt 30; 
§901(c) Amdnt 26; §903(b) (c) and (e) Amdnt 36; §908(a) Amdnt 26; §917( 
(c)(1) Rotor drive system: Design. Amdnt 40; §953(a) Amdnt 0; §1027(a) 
Amdnt 26; §1045(a)(1), (b), (c), (d), and (f) Amdnt 26; §1047(a) Amdnt 26; 
§1181(a) Amdnt 26; §1187(e) Amdnt 0; §1189(c) Amdnt 26; §1191(a)(1) 
Amdnt 3; §1193(e) Amdnt 26; §1195(a) and (d) Amdnt 17; §1197 Amdnt 13; 
§1199 Amdnt 13; §1201 Amdnt 0; §1305 (b) Amdnt 40; §1309(b) Amdnt 14; 
§1323(c)(1) Amdnt 44; §1331(b) Amdnt 24; §1587(a) Amdnt 44. 
FAR Part 36 Noise Standards amended by Amendments 36-1 through 36-21. 
DATA PERTINENT TO ALL MODELS. 
Serial Numbers Eligible. The French Government "Certificat de Navigabilite pour Exportation" 
endorsed as noted below under "Import Requirements" must be submitted for each 
individual aircraft for which application for FAA certification is made. 
Type Certificate. Type Certificate No. H11EU, issued January 19, 1981. 
Amended November 20, 1981 to add Model AS355F. 
Amended April 11, 1984 to add Model AS355F1. 
Amended February 13, 1987 to add Model AS355F2. 
Amended October 15, 1992 to add Model AS355N. Date of application for 
amended type certificate: February 12, 1991. 
Amended January 9, 2008 to add Model AS355NP. Date of application for ameded type 
certificate: April 6, 2007.

15 of 16 H11EU 
Import Requirements. 
The FAA can issue a U.S. airworthiness certificate based on a National AviationAuthority (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. 
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 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 H11EU and to be 
in a condition for safe operation.” 
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.” 
Equipment. The basic required equipment as prescribed in the applicable airworthiness 
regulations (See Certification Basis) must be installed in the helicopter for 
certification. Eurocopter Report No. 355A043462 lists required and 
optional equipment for the helicopter. 
In addition, the following item of equipment is required. 
EASA approved Rotorcraft Flight Manual, identified as Code B: 
1. For AS355E, Issue 1, Amendment 0, approved January 16, 1981 or later approved 
revision. 
2. For AS355F, Revision 0 approved April 14, 1981. 
Coded 81.16 or later approved revision. 
3. For AS355F1, Revision 0 approved March 15, 1984. 
Coded 84.11 or later approved revision. 
4. For AS355F2, Revision 0 approved February 13, 1987 plus Rush 
Revision 1B and specific pages marked B or later approved revision. 
5. For AS355N, Revision 2 approved October 2, 1992 and specific 
pages marked B or later approved revision. 
6. For AS355NP, Revision 0 approved January 9, 2008, with FAA unique pages 
marked B, or later approved revision. 
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 certificated empty weight and corresponding center of gravity location must 
include unusable fuel of 6.1 lb at 127.55 in for Front tank and 5.6 lb at 151.55 in for Rear tank. 
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

16 of 16 H11EU 
affect the weight and balance, refer to the Flight Manual Weight and Balance Appendix for 
instructions. 
NOTE 2. All placards indicated in the Rotorcraft Flight Manual must be installed in the appropriate location. 
NOTE 3. 
NOTE 4. 
NOTE 5. 
Information essential to the proper maintenance of the helicopter is contained in the manufacturer's 
AS355 Maintenance Manual provided with each helicopter. Life-limited components and associated 
retirement times are presented in Chapter 5, Section CD 5.99, and must be replaced in accordance therewith. 
Service Bulletin No. 01.02 to be used to convert 355E version of 355F version (VFR). 
Service Bulletin No. 01.09 to be used to convert 355F version to 355F1 version. 
NOTE 6. Model AS355F2 must be equipped with an approved autorelight system to be eligible for IFR certification 
below + 5º C. OAT. 
NOTE 7. Effective January 1, 2014, Eurocopter France name was changed to Airbus Helicopters. 
.....END.....
```

## ADs (131, first 50, in force first)

- [AD 2026-20-03](https://openairdocs.org/ad/2026-20-03): Placards and Markings · Airbus Helicopters AS350B, AS350BA, AS350B1 and 11 more. Effective Nov 5, 2026
- [AD 2026-20-08](https://openairdocs.org/ad/2026-20-08): Tail rotor drive system · Airbus Helicopters AS355E, AS355F, AS355F1 and 2 more. Effective Nov 5, 2026
- [AD 2026-16-03](https://openairdocs.org/ad/2026-16-03): Tail Rotor Drive System · Airbus Helicopters AS355E, AS355F, AS355F1 and 2 more. Effective Sep 17, 2026
- [AD 2026-09-15](https://openairdocs.org/ad/2026-09-15): Tail rotor head · Airbus Helicopters AS350B, AS350BA, AS350B1 and 9 more. Effective Jul 21, 2026
- [AD 2026-10-16](https://openairdocs.org/ad/2026-10-16): Time Limits/Maintenance Checks · Airbus Helicopters AS355E, AS355F, AS355F1 and 3 more. Effective Jul 21, 2026
- [AD 2026-12-03](https://openairdocs.org/ad/2026-12-03): Main rotor gearbox · Airbus Helicopters AS350B, AS350B1, AS350B2 and 11 more. Effective Jul 14, 2026
- [AD 2026-05-09](https://openairdocs.org/ad/2026-05-09): Powerplant/Engine Drains · Airbus Helicopters AS355E, AS355F, AS355F1 and 3 more. Effective Mar 25, 2026
- [AD 2025-24-04](https://openairdocs.org/ad/2025-24-04): Vertical Stabilizer, Spar/Rib Structure · Airbus Helicopters AS350B3, AS355E, AS355F and 4 more. Effective Jan 12, 2026
- [AD 2025-24-06](https://openairdocs.org/ad/2025-24-06): Cabin Equipment/Furnishings · Airbus Helicopters AS350B2, AS350B3, AS355N and 2 more. Effective Jan 12, 2026
- [AD 2025-09-13](https://openairdocs.org/ad/2025-09-13): Doors · Airbus Helicopters AS350B, AS350BA, AS350B1 and 9 more. Effective Jul 7, 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 2024-20-07](https://openairdocs.org/ad/2024-20-07): Emergency Equipment; Emergency Flotation Section · Apical Emergency Float Kit, P/N 20498 (STC SR00780LA or 12 others). Effective Dec 5, 2024
- [AD 2024-15-08](https://openairdocs.org/ad/2024-15-08): Main Rotor Blades · Airbus Helicopters AS350B, AS350BA, AS350B1 and 7 more. Effective Oct 15, 2024
- [AD 2023-11-07](https://openairdocs.org/ad/2023-11-07): Ground Proximity System · Airbus Helicopters 47, 206, 210 and 237 more. Effective Jun 22, 2023
- [AD 2023-03-13](https://openairdocs.org/ad/2023-03-13): Tail Rotor Drive System · Airbus Helicopters AS355E, AS355F, AS355F1 and 2 more. Effective Mar 31, 2023
- [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 2022-10-51](https://openairdocs.org/ad/2022-10-51): Flight Control System · Airbus Helicopters AS350B, AS350B1, AS350B2 and 22 more. Effective Jun 7, 2022
- [AD 2021-03-16 R1](https://openairdocs.org/ad/2021-03-16-R1): Passenger/Crew Doors · Airbus Helicopters AS350B, AS350B1, AS350B2 and 9 more. Effective Mar 24, 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 2021-24-03](https://openairdocs.org/ad/2021-24-03): Rotorcraft Flight Control · Airbus Helicopters AS355NP. Effective Jan 13, 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 2021-20-06](https://openairdocs.org/ad/2021-20-06): Turbine section · Airbus Helicopters AS355E, AS355F, AS355F1 and 1 more. Effective Nov 22, 2021
- [AD 2021-19-09](https://openairdocs.org/ad/2021-19-09): Cabin Equipment/Furnishings · Airbus Helicopters AS355E, AS355F, AS355F1 and 6 more. Effective Nov 4, 2021
- [AD 2021-16-16](https://openairdocs.org/ad/2021-16-16): Rotorcraft Flight Control · Airbus Helicopters AS355E, AS355F, AS355F1 and 9 more. Effective Oct 13, 2021
- [AD 2021-16-11](https://openairdocs.org/ad/2021-16-11): Tail Rotor Control System · Airbus Helicopters AS355E, AS355F, AS355F1 and 9 more. Effective Oct 6, 2021
- [AD 2021-14-07](https://openairdocs.org/ad/2021-14-07): Cabin Equipment/Furnishings · Airbus Helicopters AS332C, AS332C1, AS332L and 12 more. Effective Aug 19, 2021
- [AD 2021-07-15](https://openairdocs.org/ad/2021-07-15): Tail Rotor Drive Shaft · Airbus Helicopters AS355E, AS355F, AS355F1 and 11 more. Effective May 7, 2021
- [AD 2021-05-09](https://openairdocs.org/ad/2021-05-09): Tail Rotor Control System · Airbus Helicopters AS355E, AS355F, AS355F1 and 8 more. Effective Apr 16, 2021
- [AD 2021-04-13](https://openairdocs.org/ad/2021-04-13): Main Rotor Mast Inner Race Rings · Airbus Helicopters AS355E, AS355F, AS355F1 and 11 more. Effective Apr 14, 2021
- [AD 2021-04-17](https://openairdocs.org/ad/2021-04-17): Tail Rotor Blades · Airbus Helicopters AS355E, AS355F, AS355F1 and 7 more. Effective Mar 23, 2021
- [AD 2020-22-20](https://openairdocs.org/ad/2020-22-20): Main Rotor Gearbox · Airbus Helicopters AS355E, AS355F, AS355F1 and 12 more. Effective Dec 14, 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 2015-17-01 R1](https://openairdocs.org/ad/2015-17-01-R1): Tail Rotor · Airbus Helicopters AS355E, AS355F, AS355F1 and 11 more. Effective Sep 11, 2020
- [AD 2020-09-02](https://openairdocs.org/ad/2020-09-02): Cabin Equipment/Furnishings · Airbus Helicopters AS355NP, Model 358 Torso Restraint System, AS350B2 and 3 more. Effective May 29, 2020
- [AD 2020-09-01](https://openairdocs.org/ad/2020-09-01): Main Rotor Gearbox · Airbus Helicopters AS355E, AS355F, AS355F1 and 2 more. Effective May 28, 2020
- [AD 2020-02-23](https://openairdocs.org/ad/2020-02-23): Landing gear · Emergency Floats (Dart Aerospace ULC STC SR00470LA or SR00645LA). Effective Feb 28, 2020
- [AD 2018-19-10](https://openairdocs.org/ad/2018-19-10): Tail Rotor Driveshaft · Airbus Helicopters AS355E, AS355F, AS355F1 and 2 more. Effective Oct 30, 2018
- [AD 2018-02-02](https://openairdocs.org/ad/2018-02-02): Main Gearbox Mast · Airbus Helicopters AS355E, AS355F, AS355F1 and 11 more. Effective Feb 12, 2018
- [AD 2016-25-20](https://openairdocs.org/ad/2016-25-20): Main Rotor Drive System · Airbus Helicopters AS355E, AS355F, AS355F1 and 13 more. Effective Jan 31, 2017
- [AD 2016-25-28](https://openairdocs.org/ad/2016-25-28): Extinguishing System · Airbus Helicopters AS355NP. Effective Jan 31, 2017
- [AD 2016-05-06](https://openairdocs.org/ad/2016-05-06): Rotorcraft tailboom · Airbus Helicopters AS355E, AS355F, AS355F1 and 11 more. Effective Apr 8, 2016
- [AD 2015-17-11](https://openairdocs.org/ad/2015-17-11): Main Rotor System · Airbus Helicopters AS355E, AS355F, AS355F1 and 13 more. Effective Sep 29, 2015
- [AD 2015-12-01](https://openairdocs.org/ad/2015-12-01): Fuel Flow Sensor · Airbus Helicopters AS355E, AS355F, AS355F1 and 1 more. Effective Jul 14, 2015
- [AD 2014-05-10](https://openairdocs.org/ad/2014-05-10): Tail Rotor · Airbus Helicopters AS355E, AS355F, AS355F1 and 11 more. Effective May 2, 2014
- [AD 2014-05-07](https://openairdocs.org/ad/2014-05-07): Tail Rotor Control System · Airbus Helicopters AS355E, AS355F, AS355F1 and 9 more. Effective Apr 15, 2014
- [AD 2014-04-11](https://openairdocs.org/ad/2014-04-11): Tail rotor blades · Airbus Helicopters AS355E, AS355F, AS355F1 and 8 more. Effective Apr 9, 2014
- [AD 2013-23-10](https://openairdocs.org/ad/2013-23-10): Fuselage Miscellaneous Structure · Airbus Helicopters AS355E, AS355F, AS355F1 and 8 more. Effective Dec 30, 2013
- [AD 2013-23-09](https://openairdocs.org/ad/2013-23-09): Doors · Airbus Helicopters AS355E, AS355F, AS355F1 and 11 more. Effective Dec 27, 2013
- [AD 2013-16-03](https://openairdocs.org/ad/2013-16-03): Tail Rotor Gearbox · Airbus Helicopters AS355E, AS355F, AS355F1 and 11 more. Effective Oct 22, 2013
- [AD 2013-17-01](https://openairdocs.org/ad/2013-17-01): Tail rotor control system · Airbus Helicopters AS355E, AS355F, AS355F1 and 11 more. Effective Oct 9, 2013

All 131: https://openairdocs.org/tcds/H11EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Aerospatiale AS 355F1](https://openairdocs.org/model/aerospatiale-as-355f1): 9 aircraft (registry code 8680810)
- [Aerospatiale AS 355F2](https://openairdocs.org/model/aerospatiale-as-355f2): 6 aircraft (registry code 8680825)
- [Eurocopter/France AS355N TWINSTAR](https://openairdocs.org/model/eurocopter-france-as355n-twinstar): 4 aircraft (registry code 8680970)
- [Aerospatiale AS355F2 ECUREUIL](https://openairdocs.org/model/aerospatiale-as355f2-ecureuil): 3 aircraft (registry code 8680812)
- [Aerospatiale AS355F TWINSTAR](https://openairdocs.org/model/aerospatiale-as355f-twinstar): 2 aircraft (registry code 8680807)
- [Airbus Helicopters AS355N](https://openairdocs.org/model/airbus-helicopters-as355n): 2 aircraft (registry code 8680775)
- [Aerospatiale AS 355 F ECUREUIL](https://openairdocs.org/model/aerospatiale-as-355-f-ecureuil): 1 aircraft (registry code 8680806)
- [Aerospatiale AS-355E TWIN STAR](https://openairdocs.org/model/aerospatiale-as-355e-twin-star): 1 aircraft (registry code 8680805)
- [Aerospatiale AS355N](https://openairdocs.org/model/aerospatiale-as355n): 1 aircraft (registry code 8680871)
- [Airbus Helicopter AS355F1](https://openairdocs.org/model/airbus-helicopter-as355f1): 1 aircraft (registry code 8680835)
- [Airbus Helicopters AS355F2](https://openairdocs.org/model/airbus-helicopters-as355f2): 1 aircraft (registry code 8680971)
- [Eurocopter AS 355N](https://openairdocs.org/model/eurocopter-as-355n): 1 aircraft (registry code 8680966)
- [Eurocopter AS355NP](https://openairdocs.org/model/eurocopter-as355np): 1 aircraft (registry code 8680777)
- [Eurocopter France AS355F2](https://openairdocs.org/model/eurocopter-france-as355f2): 1 aircraft (registry code 8680976)
- [S N I A S AS 355F](https://openairdocs.org/model/s-n-i-a-s-as-355f): 1 aircraft (registry code 8680850)
- [Aerospatiale AS 355F](https://openairdocs.org/model/aerospatiale-as-355f): 0 aircraft (registry code 8680851)
- [Airbus Helicopters AS355NP](https://openairdocs.org/model/airbus-helicopters-as355np): 0 aircraft (registry code 8680778)
- [Eurocopter France AS355F1](https://openairdocs.org/model/eurocopter-france-as355f1): 0 aircraft (registry code 8680979)
- [S N I A S AS355 F2](https://openairdocs.org/model/s-n-i-a-s-as355-f2): 0 aircraft (registry code 8680613)

## STCs approved under this data sheet (324, first 50)

- [STC SH4716NM](https://openairdocs.org/stc/SH4716NM): Redesign and relocation of cargo door hinges and relocation of cargo door latch. Turbolyft USA Corporation
- [STC SR00219SE](https://openairdocs.org/stc/SR00219SE): Installation of a color video camera on either the left, right, or both upper outboard surfaces of the horizontal stabilizer. Turbolyft USA Corporation
- [STC SR00242SE](https://openairdocs.org/stc/SR00242SE): Fabrication and Installation of a new instrument panel and pedestal. Turbolyft USA Corporation
- [STC SR00326SE](https://openairdocs.org/stc/SR00326SE): Installation of Geneva Aviation Microwave System. Turbolyft USA Corporation
- [STC SR00361SE](https://openairdocs.org/stc/SR00361SE): Installation of baggage compartment utility rack.. Turbolyft USA Corporation
- [STC SR00474SE](https://openairdocs.org/stc/SR00474SE): Installation of a modular equipment rack in the left side only, right side only, or both side cargo compartments.. Turbolyft USA Corporation
- [STC SR00643SE](https://openairdocs.org/stc/SR00643SE): Installation of Geneva Aviation Video System. Turbolyft USA Corporation
- [STC SR04464NY](https://openairdocs.org/stc/SR04464NY): Installation of the iPad Mount. Avio Design Group Inc.
- [STC SR00521SE](https://openairdocs.org/stc/SR00521SE): Installation of Geneva Aviation Audio System. AEM USA Inc.
- [STC SR02301SE](https://openairdocs.org/stc/SR02301SE): Installation of Geneva Aviation 28 - 14 VDC Power Converter. AEM USA Inc.
- [STC SR02445SE](https://openairdocs.org/stc/SR02445SE): Installation of P178 Failsafe Audio Mixer. AEM USA Inc.
- [STC SR00307DE](https://openairdocs.org/stc/SR00307DE): Installation of Aft Jump Seat. Air Methods LLC
- [STC SR00308DE](https://openairdocs.org/stc/SR00308DE): Installation of Composite Interior. Air Methods LLC
- [STC SR04644CH](https://openairdocs.org/stc/SR04644CH): Replacement of existing main ship battery with Lithium Ion Battery and installation of Battery System Annunciator. Airwolf Aerospace LLC
- [STC SR12092IB](https://openairdocs.org/stc/SR12092IB): Manufacturing and Installation of Cargo Hold Nets. ICARUS AERO INC.
- [STC SR00425SE](https://openairdocs.org/stc/SR00425SE): Installation of a satellite phone.. Turbolyft USA Corporation
- [STC SR00184IB](https://openairdocs.org/stc/SR00184IB): Installation of External Cargo Basket and Boarding Step. Boost Human External Cargo Systems Inc.
- [STC SR00182IB](https://openairdocs.org/stc/SR00182IB): Installation of the Avidyne Integrated Flight Display (IFD) Navigator(s). Horizon Design Services Ltd.
- [STC SR04637CH](https://openairdocs.org/stc/SR04637CH): Replacement of existing main ship battery with Lithium Ion Battery and installation of Annunciator Control
Panel. Airwolf Aerospace LLC
- [STC SR00125DE](https://openairdocs.org/stc/SR00125DE): Installation of infrared imaging system. Dart Aerospace Company
- [STC SH2510SO](https://openairdocs.org/stc/SH2510SO): Installation of a camera mount and photographer's seat.. Ephraim Nowak
- [STC SR00133DE](https://openairdocs.org/stc/SR00133DE): Installation of external pod and camera mount.. Dart Aerospace USA Inc.
- [STC SR00416DE](https://openairdocs.org/stc/SR00416DE): Installation of laser mapping system.. Dart Aerospace USA Inc.
- [STC SR00118IB](https://openairdocs.org/stc/SR00118IB): Manufacture of Cargo Hook Mount for Side Pull Operations. Mustang Helicopters Inc.
- [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 SR00645LA](https://openairdocs.org/stc/SR00645LA): Installation of emergency floats.. Dart Aerospace ULC
- [STC SR04557NY](https://openairdocs.org/stc/SR04557NY): Installation of the Fuel Cap Replacement. Avio Design Group Inc
- [STC SR00091IB](https://openairdocs.org/stc/SR00091IB): Installation of the Bear Paw Kit. Alpine Aerotech LP
- [STC SR04669NY](https://openairdocs.org/stc/SR04669NY): Installation of Human External Cargo Y-Rope and Long-Line Kit. Boost Human External Cargo Systems Inc
- [STC SR01424SE](https://openairdocs.org/stc/SR01424SE): Fabrication of Onboard Systems Model 200-292-01 Cargo Hook Kit and Model 200-292-02 Cargo Hook Kit. Onboard Systems International LLC
- [STC SR02035SE](https://openairdocs.org/stc/SR02035SE): Fabrication of Onboard Systems International Model 200-352-00, Cargo Hook Kit. Onboard Systems International LLC
- [STC SH4846SW](https://openairdocs.org/stc/SH4846SW): Installation of formed plexiglass windshield.. The NORDAM Group LLC
- [STC SR02704SE](https://openairdocs.org/stc/SR02704SE): Installation and maintenance of the Sunspot 36 and 46 series lights. AeroLED's Holdings LLC
- [STC SR02230AK](https://openairdocs.org/stc/SR02230AK): Installation of Chelton Flight Systems FlightLogic Electronic Flight Instrument System (EFIS). Genesys Aerosystems Inc.
- [STC SR02770NY](https://openairdocs.org/stc/SR02770NY): The installation of Quick Release Maintenance Step, Maintenance Peg Step and Fixed Cabin Step. Dart Aerospace Limited
- [STC SR03913NY](https://openairdocs.org/stc/SR03913NY): The installation of Quick Release Bicycle Rack. Dart Aerospace Limited
- [STC SR02680NY](https://openairdocs.org/stc/SR02680NY): The installation of External Attachement Provisions and Cargo Basket to. Dart Aerospace Limited
- [STC SR00457NY](https://openairdocs.org/stc/SR00457NY): Installation of a left-hand or right-hand cargo mirror.. Airbus Helicopters Canada Limited
- [STC SH304NM](https://openairdocs.org/stc/SH304NM): Installation of a Sperry single pilot IFR AFCS (Category 1).. Honeywell International Inc
- [STC SH305NM](https://openairdocs.org/stc/SH305NM): Installation of a Sperry Primus 300 SL weather radar system.. Honeywell International Inc
- [STC SR02124SE](https://openairdocs.org/stc/SR02124SE): Installation functionality. of Data Garmin Required: transponders: (1) Garmin GTX Master 345/345R Drawing with List ADS-B (MDL), Out and In 005-00734-A4, functionality;. Garmin International Inc
- [STC SR02432NY](https://openairdocs.org/stc/SR02432NY): Installation of Helitowcart Bear Paw Models BP350, BP44 or BP130. Dart Aerospace Ltd.
- [STC SR00359BO](https://openairdocs.org/stc/SR00359BO): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SR00699LA](https://openairdocs.org/stc/SR00699LA): Installation of medical system.. LifePort LLC
- [STC SR09145RC](https://openairdocs.org/stc/SR09145RC): Installation of an air medical system.. LifePort LLC
- [STC SR00600NY](https://openairdocs.org/stc/SR00600NY): Installation of skid mounted cargo baskets.. Dart Aerospace Limited
- [STC SR00012SE](https://openairdocs.org/stc/SR00012SE): Installation of LifePort patient loading and support system.. LifePort LLC
- [STC SR00821DE](https://openairdocs.org/stc/SR00821DE): Installation of Automatic Dependent Surveillance - Broadcast (ADS-B) Out and in functionality using the BendixKing KT74 Transponder and qualified position sensor and ADS-B In Receiver. Peregrine
- [STC SR00795NY](https://openairdocs.org/stc/SR00795NY): Installation of LH and/or RH "Squirrel Cheeks" Cargo Pods. Airbus Helicopters Canada Limited
- [STC SR00211SE](https://openairdocs.org/stc/SR00211SE): Fabrication and Installation of rear seat shoulder harnesses. Dart Aerospace USA Inc.

All 324: https://openairdocs.org/tcds/H11EU/stcs.md

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