# TCDS H9EU: Airbus Helicopters

- Type: Type certificate data sheet
- Status: Current
- Holder: Airbus Helicopters
- Revision: 26
- Revised: June 14, 2021
- Product: Aircraft, Rotorcraft
- Certification basis: Part 27, Part 21, Part 27, Part 21, Part 21, Part 27, Part 36, Part 27, Part 21, Part 27, Part 21, Part 21, Part 27, Part 36, Part 27, Part 21, Part 27, Part 21, Part 27, Part 21, Part 27, Part 21
- Registered aircraft: 1,269, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/8a/24/8a24e978f218ad5c7e6e45bf768c2f6dbe5fbcfa938aae11121c5049034711e9
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/A5D480AE073AFA93862586F1004929F8.0001
- Page: https://openairdocs.org/tcds/H9EU

## Models (10)

As the data sheet lists them.

- AS350C (ASTAR)
- AS350B3 (ECUREUIL)
- EC130B4 (ASTAR)
- AS350B (ECUREUIL)
- AS350D1 (ASTAR)
- EC130T2
- AS350B2 (ECUREUIL)
- AS350B1 (ECUREUIL)
- AS350D (ASTAR)
- AS350BA (ECUREUIL)

## What the data sheet says

Some pages are OCR from the scanned FAA data sheet. OCR can misread letters and numbers.

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
H9EU 
Revision 26 
Airbus Helicopters 
AS350C
 AS350D 
AS350D1
 AS350B
 AS350B1
 AS350B2
 AS350BA 
AS350B3
 EC130B4 
EC130T2 
June 14, 2021 
TYPE CERTIFICATE DATA SHEET NO. H9EU 
This data sheet, which is a part of Type Certificate No. H9EU, 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 Inte rnational Marseille Provence 
13725 - Marignane - Cedex
        F r a n c e 
TC Holder Record:     Euroc opter France changed name to Airbus Helicopters on January 1, 2014. 
I.   Model AS-350C “ASTAR” (Normal Category) Helicopter, approved December 21, 1977. 
Engine. 1. Lycoming LTS 101 600A with Bendix power turbine governor
          Lycoming P/N 4.301.101.04 
Fuel. - Normal fuels: Kerose ne, MIL-T-5624 (JP5); ASTM D1655 jet A and A1
 - Wide Cut:  MIL-T-5624 (JP4); STM D1655 Jet B
 - E m e r g e n c y F u e l :
         (Maximum viscosity: 12 centistokes (See corresponding limitations in 
         L y c o m i n g i n s t a l l a t i o n m a nual under “Installation Instructions”). 
Oil. - Automotive Diesel Fuel: ASTM D975 (N° 2D) or lighter
 - Synthetic oil (5 Cst) MIL.L.23699
 - Synthetic oil (3 Cst) MIL.L.7808
         Mixing of these oils are not permitted. 
E n g i n e L i m i t s .  - P o wer Ratings (Sea Level, ISA) 
           Takeoff (5 mn) 592 shp. 
           Max. Continuous 505 shp. 
- G a s G e n e r a t o r S p e e d s
           Takeoff (5 mn) 48,825 rpm (102%) 
Max.Continuous 48,060 rpm (100.4%)
           Transient   49,685 rpm (103.8%)
 - Engine Gear Box Limitations
 Takeoff   592 shp. 
           Max. Continuous 505 shp. 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 
Rev. No. 25 25 25 13 13 8 7 18 18 18 25 25 25 25 19 25 25 
Page No. 18 19 20 21 22 
Rev. No. 26 25 18 25 25

2 of 22 H9EU, Rev. 26 
Engine Limits. (Cont’d) - Exhaust Gas Temperature (T4)
 Takeoff  706°C 
           Max. Continuous 732°C 
           Transient 843°C 
           Starting Max.* 899°C 
* Time Limit 12 seconds above 799°C 
T r a n s m i s s i o n L i m i t s .             T O R Q U E  S H P .  K W .
         Maximum takeoff power (5 mn) 101% 531 396 
         Maximum continuous 101% 531 396 
Helicopter Limits.      Maximum takeoff (5 mn)  101% 531 396 
         Maximum continuous 96%  505 377 
Maximum Weight.      4300 lb. (see NOTE 6) 
Serial Numbers. No eligible serial numbers. (see NOTE 14) 
II.   Model AS-350D “ASTAR” (Normal Category) Helicopter, approved July 6, 1978. 
Same as Model AS-350C except for more powerful LTS 101 600A2 engine. 
Engine. 1. Lycoming LTS 101-600A-2 
- Normal Fuels: Kerosene; MIL-T-5624 (JP5); ASTM D1655 Jet A and A1
 - Wide Cut:  MIL-T-5624 (JP4); ASTM D1655 Jet B
 - E m e r g e n c y F u e l :
 - Automotive Diesel Fuel: ASTM D975 (N° 2D) of lighter. 
- Synthetic oil (5 Cst) MIL.L.23699
 - Synthetic oil (3 Cst) MIL.L.7808
         Mixing of these oils is not permitted. 
E n g i n e L i m i t s .  - P o wer Ratings (Sea Level , ISA) 
           Takeoff (5 min.)   615 shp. 
           Max. Continuous   590 shp. 
- G a s G e n e r a t o r S p e e d s
           Takeoff (5 mn) 49,638 rpm 
Max.Continuous 49,159 rpm 
           Transient   50,548 rpm 
. 
- Exhaust Gas Temperature (T4)
 Takeoff  771°C 
           Max. Continuous 760°C 
           Transient Max. * 843°C 
           Starting Max. *  899°C 
* Time limit 12 seconds above 818°C 
T r a n s m i s s i o n L i m i t s .             T O R Q U E  S H P   K W
         Maximum takeoff power (5 min)  101% 531 396 
         Maximum Continuous 101% 531 396 
Helicopter Limits. Torque
         O t h e r L i m i t s
 : 
: 
Same as transmission limits 
S a m e a s e n g i n e l i m i t s e x c e p t f o r :
           Max. continuous gas generator speed 48,930 r.p.m. (102.2%)
           Max. continuous gas temperature 744°C 
Maximum Weight.      4300 lb (See NOTE 6).

3 of 22 H9EU, Rev. 26 
III.   Model AS-350D1 “ASTAR” (Normal Category) Helicopter, approved August 4, 1978. 
  Same as Model AS 350D except for maximum weight. 
Maximum Weight. 4000 lb (See NOTE 5) 
Serial Numbers. No eligible serial numbers. (see NOTE 15) 
IV.  Model AS-350B “ECUREUIL” (Normal Category) Helicopter, approved November 9, 1978. 
Engine.       1 TURBOMECA Arriel 1B 
Fuel. - Normal Fuels: Kerosene; MIL-T-83133; ASTM D1655 Jet A1, Jet A
 - Wide Cut (JP4), MIL-T-5624; ASTM D1655 Jet B 
        High flash point (JP 5); MIL-T-5624 
- E m e r g e n c y F u e l S e e N O T E 
Oil. - Synthetic oil (5 Cst)  MIL.L.23699
 - Synthetic oil (3 Cst)  MIL.L.7808
 - S y n t h e t i c o i l ( 3 C s t )
 - S y n t h e t i c o i l ( 3 . 9 C s t )    A e r o s h e l l T u r b i n e O i l 3 9 0
        Mixing of these oils is not permitted. 
Engine Limits. - Power Ratings (Sea Level, ISA) 
          Takeoff (5 min)   641 shp. 
          Max. Continuous   590 shp. 
- G a s G e n e r a t o r S p e e d s ( S e a L e v e l ) , I S A
 Takeoff     51,800 rpm (100%) 
          Max. Continuous   50,750 rpm ( 98%) 
          Transient     54,400 rpm (105%) 
- Engine Gear Box Limitations 
Max. torque stabilized 109% (100% corresponds to 641 shp at 6,000 rpm 
p o w e r s h a f t s p e e d )
 - Exhaust Gas Temperature (T4)
 Takeoff  810°C 
          Max. Continuous 775°C 
          Starting max. 840°C 
T r a n s m i s s i o n L i m i t s .            T O R Q U E  S H P   K W
        Maximum takeoff power (5 min)  83% 531 396 
        Maximum continuous 83% 531 396 
Helicopter Limits.     Maximum take off (5 min)  83% 531 396 
        Maximum continuous 83% 531 396 
Maximum Weight. 4300 lb (see NOTE 6) 
V.  Model AS 350B1 “ECUREUIL” (Normal Category) Helicopter, approved February 13, 1987. 
Similar to AS 350B except Turbomeca Arriel 1D engine, main and tail rotors as AS 355F1, maximum weight, other changes. 
Engine.       1 TURBOMECA ARRIEL 1D. 
Fuel. Refer to Flight Manual AS 350B1 for approved and additive specification. 
Oil.        Refer to Flight Manual AS 350B1 for approved and additive specification.

4 of 22 H9EU, Rev. 26 
Engine Limits. - Power Ratings (Sea Level, ISA) 
          Takeoff (5 min)   684 shp. 
          Max. Continuous   603 shp. 
- G a s G e n e r a t o r S p e e d s ( S e a L e v e l , I S A )
 Takeoff  52,215 (100.8%)
          Max. Continuous 50,764 ( 98%)
          Transient 54,650 (105.5%)
 - Engine Gear Box Limitations 
Max. torque stabilized 109.2% (100% corresponds to 641 shp at 6000 rpm 
p o w e r s h a f t s p e e d )
 - Exhaust Gas Temperature (T4)
 Takeoff  845°C 
          Max. Continuous 795°C 
          Starting Max. 865°C 
H e l i c o p t e r L i m i t s .
        Maximum torque = IAS 40 knots or higher 
            IAS below 40 knots 
              T O R Q U E K W
94%  450 
100%  478 
Maximum Weight. 4850 lb (See NOTE 6) 
C.G. Range.      Longitudinal 
        L a t e r a l
        R i g h t 5 . 5 1 i n
        L e f t 7 . 0 8 i n 
Rotor Speeds.      In autorotation
        Maximum 430 rpm 
        Minimum 320 rpm 
        In power-on flight   390 + 4 rpm 
- 5 r p m 
Rotor Low Speed Warning. Aural at 360 rpm.

5 of 22 H9EU, Rev. 26 
Airspeed Limits.     Never exceed speed V NE power on: 
        155 Kt at Zero pressure altitude
        Never exceed speed V NE power-off: 
        125 Kt at Zero pressure altitude
        S e e R o t o r c r a f t F l i g h t M a n u a l f o r d e c r e a se of these values with altitude and temperature. 
VI.  Model AS 350B2 “ECUREUIL” (Normal Category) Helicopter, approved June 8, 1990. 
  Similar as to AS350B1 except Turbomeca ARRIEL 1D1 engine, maximum weight, other changes. 
Engine.       1 TURBOMECA ARRIEL 1D1 
Fuel. Refer to Flight Manual AS 350B2 for approved and additive specification. 
Oil.        Refer to Flight Manual AS 350B2 for approved and additive specification. 
Engine Limits. - Power Ratings (Sea Level, ISA) 
          Takeoff (5 min)   712 shp. 
Max.Continuous   625 shp. 
- G a s G e n e r a t o r S p e e d s ( S e a L e v e l , I S A )
 Takeoff  52,784 (101.9%)
          Max. Continuous 50,764 ( 98%)
          Transient 54,650 (105.5%)
 - Engine Gear Box Limitations 
Max. torque stabilized 109.2% (100% corresponds to 641 shp at 6000 rpm 
p o w e r s h a f t s p e e d ) 
- Exhaust Gas Temperature (T4)
 Takeoff
          Max. Continuous 
          Starting Max. 
845°C 
795°C 
865°C 
H e l i c o p t e r L i m i t s .              T O R Q U E S H P 
Maximum torque = IAS 40 knots or higher  94%
       IAS below 40 knots 100%  641 
Maximum Weight. 4961 lb (See NOTE 6) 
C.G. Range.      Longitudinal

6 of 22 H9EU, Rev. 26
        L a t e r a l
 Right 
        L e f t
5.51 in
 7 . 0 8 i n 
Rotor Speeds. 
Rotor Speed Warning. 
Airspeed Limits.
     In autorotation
        Maximum 430 rpm 
        Minimum 320 rpm 
        In Power-on flight   390 + 4 rpm 
- 5 r p m 
Aural at 360 rpm and 410 rpm 
    Never exceed speed V NE power on: 
        155 Kt at zero pressure altitude
        Never exceed speed V NE power off: 
        125 Kt at zero pressure altitude
        S e e R o t o r c r a f t F l i g h t M a n u a l f o r d e c r e a se of these values with altitude and temperature. 
VII.  Model AS 350BA “ECUREUIL” (Normal Category) Helicopter, approved March 11, 1992. 
  Same as Model AS 350B except for 355 type main rotor blades. 
Other Changes. 
Helicopter Limits Vi (I.A.S.) Torque Kw RPM 
Maximum torque limit 
Maximum continuous torque 
 Reference 
<40 Kt 
>40 Kt 
88% 
83% 
100% 
396 
478 
386 
386 
Maximum Weight. 4630 lb (See NOTE 6). 
C.G. Range.      Longitudinal 
       L a t e r a l :
        R i g h t L i m i t :  5 . 5 1 i n .
        L e f t L i m i t :  7 . 0 8 i n . 
Rotor Speeds.      The same as 350B1. 
Rotor Low Speed Warning. The same as AS350B1.

7 of 22 H9EU, Rev. 26 
Airspeed Limits.     The same as AS350B1.  See Rotorcraft Flight Manual for decrease of the values with 
        altitude and temperature. 
Versions 350B, C, D and D1 Common Particulars 
Rotor Speeds.      In Autorotation
 Maximum 
Minimum 
  424 rpm 
320 rpm 
        In power-on Flight  385 + 1 rpm 
- 5 r p m 
Rotor Low-Speed Warning. Aural at - 335 rpm (See NOTE 8) 
Airspeed Limits. Never-exceed-speed:  147 kt from S.L. to 1000 feet, then decreasing with altitude 3.5 kt 
for each 1000 feet density altitude above 1000 feet.  For operations below -30°C ambient 
        temperature, decrease above V NE schedule by 10 kts. 
C . G . R a n g e .      F w d L i m i t  A f t L i m i t
        L o n g i t u d i n a l
 124.8 in.    139.7 in. to 2,865 lb. 
135.0 in. to 4,190 lb. 
             L i n e a r variation between points shown. 
135.0 in. from 4,190 lb. to 4,300 lb. 
        L a t e r a l
        R i g h t 3 . 1 4 i n .
        L e f t 5 . 9 0 i n . 
VIII.  Model AS 350B3 “ECUREUIL” (Normal Category) Helicopter, approved May 7, 1998. 
  Similar as to AS350B2 except Turbomeca ARRIEL 2B, 2B1, or 2D engine with FADEC 
Engine.       1TURBOMECA ARRIEL 2B, 
        1 T U R B O M E C A A R R I E L 2 B 1 , o r
        1 T U R B O M E C A A R R I E L 2 D . 
Fuel. Refer to Flight Manuals AS 350B3 for approved and additive specification. 
Oil.        Refer to Flight Manuals AS  350B3 for approved and additive specification. 
Engine Limits (Arriel 2B or 2B1). - Power Ratings (Sea Level, ISA) 
          Takeoff (5 min)   747 shp. 
Max.Continuous   728 shp. 
- G a s G e n e r a t o r S p e e d s ( S e a L e v e l , I S A )
 Takeoff  52,756 (101.2%)
          Max. Continuous 50,672 ( 97.2%)
 - Engine Gear Box Limitations
        Refer to Engine TCDS E00054EN 
- Exhaust Gas Temperature (T4)
 Takeoff
          Max. Continuous 
          Starting Max. 
915°C 
849°C 
865°C 
Engine Limits (Arriel2D)  - Power Ratings (Sea Level, ISA) 
          Takeoff (5 min)   747 shp. 
          Max. Continuous   728 shp. 
- G a s G e n e r a t o r S p e e d s ( S e a L e v e l , I S A )
 Takeoff  52,579 (100.9%)
          Max. Continuous 51,067 ( 97.2%)

8 of 22 H9EU, Rev. 26 
- Engine Gear Box Limitations
 - Exhaust Gas Temperature (T4)
          T a k e o f f     9 4 9 ° C
          M a x . C o n t i n u o u s   9 0 5 ° C
          S t a r t i n g M a x .    8 4 0 ° C 
Note : The indicated limits are engine limits when installed in the AS350B3. Refer to Engine TCDS for the Engine limits 
Helicopter Limits (Arriel2B engine mounted pre-mod. AMS 072803 and 072808). TORQUE 
        Maximum torque = IAS 40 knots or higher 84%
       I A S b e l o w 4 0 k n o t s 1 0 0 % 
Helicopter Limits (Arriel2B engine mounted and post-mod. AMS 072803 and 072808) TORQUE 
        Maximum torque = IAS 40 knots or higher 92.7%
 I A S b e l o w 4 0 k n o t s 1 0 0 % 
Helicopter Limits (Arriel2B1 engine mounted)  TORQUE 
        Maximum torque = IAS 40 knots or higher 92.7%
 I A S b e l o w 4 0 k n o t s 1 0 0 % 
Helicopter Limits (Arriel2D engine mounted) .         T O R Q U E 
        Maximum torque = IAS 40 knots or higher 92.7%
 I A S b e l o w 4 0 k n o t s 1 0 0 % 
Maximum Weight. 4960 lb (See NOTE 6).
        5220 lb for a/c incorporating mod. OP-3369. 
C . G . R a n g e .  L ongitudinal: AS350 B3 ARRIEL 2B1 a/c incorporating mod. OP-3369:
 Longitudinal: AS350 B3 ARRIEL 2B  (before modifications AMS 072803 and 072808) and 
        for AS 350 B3 ARRIEL 2B1:

9 of 22  HEU, Rev. 26
C.G. (m)
3.49
3.35  3.40  3.45
2250) -  S(KX) 4961
22(x)
4409
Weight (kg)  Weight (Ibs)
AFT LIMIT  - 35(X)
< FORWARD LIMIT  L SA
2646
126.4  132  134  136
134.8
CG (in)
Longitudinal: AS350 B3 ARRIEL 2B (after modifications AMS 072803 and 072808):
CG (m)  3.00
3.25  3.30  3.40  3.45
5(XX) 4961
22(x)
45(X)
18(X)  _4(Xx)
Weight (kg)  Weight (Ibs)
1600
AFTLIMIT  - 35(x)
1400
< FORWARD LIMIT
132  136
134.8  137.4
124.8]  CG (in)  137.8
Longitudinal: AS350 B3 ARRIEL 2D a/c incorporating mod. OP-3369:

10 of 22  HEU, Rev. 26
CG ( m )
3.17  3.23  3.407  3.49  3.498
2800  3.20  3.24  3.28  3.32  3.36  3.40  3.46  • 6173
2600-
5500
WEIGHT ( kg )  2200  2370  - 5225  WEIGHT ( lb )
4500
2000  4409
4000
1750  3858
REARWARD LIMIT
1600  3500
1400
MV.50.0516.02  1310  FORWARD LIMIT  3000  12888
1200  2646
124  126  128  130  132  134  136  138
124.8  127.2  134.1  137.4 137.7
CG (in )
Longitudinal: AS350 B3 ARRIEL 2D:
3.17  3.21  CG (m)  3.425  3.49  3.498
3.20  3.30  3.40
2250  - 4961
WEIGHT ( kg )  4500
2000  4409
1800  4000
1750  3858
1600 -  REARWARD LIMIT  3500
1400  FORWARD LIMIT  3000
1310  2888
1200  2646
124  126  128  130 132  134  136  138
124.8  126.4  134.8  137.4 137.7
CG ( in )
Lateral
L.H. limit:  0.18 m (7.08 in) up to 2250 kg and
0.08 m (3.15 in) from 2250 up to 2370 kg for a/c incorporating mod. OP-3369
R.H. limit:  0.14 m (5.51 in) up to 2250 kg and
0.08 m (3.15 in) from 2250 up to 2370 kg for a/c incorporating mod. OP-3369
Rotor Speeds.  In autorotation
Maximum 430 rpm
Minimum 320 rpm
In Power-on flight: With Arriel 2B390 + 4 rpm

11 of 22 H9EU, Rev. 26 
- 5 r p m
            With Arriel 2B1 390 +15 rpm
                 - 1 5 r p m
            With Arriel 2D 390 +15 rpm
                 - 1 5 r p m 
Rotor Speed Warning. Aural at 360 rpm and 410 rpm 
Airspeed Limits.     Never exceed speed V NE power on: 
        155 Kt at zero pressure altitude
        Never exceed speed V NE power off: 
        125 Kt at zero pressure altitude
        S e e R o t o r c r a f t F l i g h t M a n u a l f o r d e c r e a se of these values with altitude and temperature. 
Serial Numbers.   S/N 2968 and S/N’s 3063 and subsequent 
S/N 4201 and up for a/c incorporating mod. OP-3369 (2370 kg weight extension) 
S/N 4767 and up for a/c incorporating mod. OP-4305 (without or with mod. OP-3369) 
IX.  Model EC 130 B4 (Normal Category) Helicopter, approved December 21, 2000. 
 Similar as to AS350B3 except a gross weight increase to 2400 kg, enlarged fuselage structure utilizing some standard EC 120B 
components, and an EC 135 type fenestron anti-torque system. 
Engine       1 TURBOMECA ARRIEL 2B1 
Fuel        Refer to Flight Manual EC 130B4 for approved fuels and additive specification. 
Oil        Refer to Flight Manual EC 130 B4 for approved oils and additive specification. 
Engine Limits  - Po wer Ratings (Sea Level, ISA) 
          Takeoff (5 min)
          Max. Continuous 
 747 shp. 
 728 shp. 
- G a s G e n e r a t o r S p e e d s ( S e a L e v e l , I S A )
 Takeoff  101.1%
          Max. Continuous 97.1%
          Maximum transient 102.3%
          (note 100%= 52110 RPM) 
- Engine Gear Box Limitations
        Refer to Engine TCDS E00054EN 
- Exhaust Gas Temperature (T4)
 Takeoff (5 min.)
          Max. Continuous 
          Starting transient (10 sec) 
          Continuous starting 
915°C 
849°C 
865°C 
750°C 
Transmission Limits 
        Maximum takeoff torque – 100%
        Maximum continuous torque – 92.7%
        Maximum Transient (5 second) – 104% 
(100% based on 536 Kw at 6000 engine RPM and 386 main rotor RPM) 
Maximum Weight     2427 Kg (5350 lbs) 
Minimum Crew     1 pilot 
Maximum Passengers 6 (2 in front, four in rear) 
Option 7 passengers (3 in front, four in rear)

12 of 22 H9EU, Rev. 26 
Maximum Baggage.    Right Baggage Compartment : 287 lb.  (max distribution 62.5 lb/sq ft) 
Left Baggage Compartment : 342 lb.  (max distribution 62.5 lb/sq ft)
        Rear Baggage Compartment : 176 lb. (max distribution 30 lb/sq ft)
        Main Cabin (on rear floor) : 1091 lb. (max distribution 62.5 lb/sq ft)
  (on LH fwd floor): 893 lb.  (max distribution 62.5 lb/sq ft) 
Fuel Capacity. Total 
        U s a b l e 
: 
: 
  142.7 U.S. Gallons
1 4 2 . 3 U . S . G a l l o n s 
Oil Capacity.      Engine Tank Max. 
1 . 6 4 U . S . G a l l o n s
        M G B M a x . 1 . 9 3 U.S. Gallons (includes filter)
        T G B M a x . 0 . 1 3 U . S . G a l l o n s 
Rotor Blades and Control 
Movements. 
For rigging information, refer to the EC 130B4 Maintenance Manual. 
C.G. Range      Longitudinal 
       L a t e r a l
 Right 
       L e f t
0.10 m 
 0 . 1 0 m 
Datum Longitudinal - 3.4 m (133.8 in) forward of main rotor head
       Lateral - Symmetrical plane of the aircraft 
Leveling Means    Mechanical floor 
Rotor Speeds     In autorotation
       Maximum 430 rpm 
       Minimum 320 rpm 
       In Power-on flight 
       375 to 405 RPM 
Rotor Speed Warning Aural at 360 rpm and 410 rpm

13 of 22 H9EU, Rev. 26 
Airspeed Limits    Never exceed speed V NE power on: 
       155 Kt at sea level 
       Never exceed speed V NE power off: 
       125 Kt at sea level 
       S e e R o t o r c r a f t F l i g h t M a n u a l f o r d e c r e a s e  of these values with altitude and temperature. 
Maximum Altitude 23,000 feet pressure altitude 
Serial Numbers    S/ N’s 3358 and subsequent 
X.  Model EC 130 T2 (Normal Category) Helicopter, approved July 30, 2012. 
 Similar as to EC130 B4 except a gross weight increase to 2500 kg and a more powerful engine. 
Engine       1 TURBOMECA ARRIEL 2D 
Fuel        Refer to Flight Manual EC 130T2 for approved fuels and additive specification. 
Oil        Refer to Flight Manual EC 130 T2 for approved oils and additive specification. 
Engine Limits  - Po wer Ratings (Sea Level, ISA) 
          Takeoff (5 min)
30 minute Power rating 
          Max. Continuous 
  802 shp. 
802 shp 
  802 shp. 
- G a s G e n e r a t o r S p e e d s ( S e a L e v e l , I S A )
 Takeoff  101.9% 
30 minute Power rating 101.9% 
          Max. Continuous 99.9% 
          Maximum transient 103.0% 
(53086 rpm) 
(53086 rpm) 
(52050 rpm) 
(53658 rpm) 
          (note 100%= 52110 RPM) 
- Engine Gear Box Limitations
        Refer to Engine TCDS E00054EN 
- Exhaust Gas Temperature (T4)
 Takeoff (5 min.)
30 minute Power rating
          Max. Continuous 
          Starting transient (20 sec) 
          Continuous starting 
949°C 
949°C 
905°C 
840°C 
750°C 
Transmission Limits 
        Maximum takeoff torque – 100% 
30 minute Power rating - 100% 
        Maximum continuous torque – 81.3%
        Maximum Transient (5 second) – 104% 
(100% based on 598 Kw at 6000 engine RPM and 386 main rotor RPM) 
Maximum Weight     2500 Kg (5512 lbs) 
Minimum Crew     1 pilot 
Maximum Passengers 6 (2 in front, four in rear) 
Option 7 passengers (3 in front, four in rear)

14 of 22 H9EU, Rev. 26 
Maximum Baggage.    Right Ba ggage Compartment : 287 lb.  (max distribution 62.5 lb/sq ft)
        Left Baggage Compartment : 342 lb.  (max distribution 62.5 lb/sq ft)
        Rear Baggage Compartmen t : 176 lb. (max distribution 30 lb/sq ft)
        Main Cabin (on rear floor) : 1091 lb. (max distribution 62.5 lb/sq ft)
  (on LH fwd floor): 893 lb.  (max distribution 62.5 lb/sq ft) 
Fuel Capacity. Total 
        U s a b l e 
: 
: 
  142.7 U.S. Gallons
1 4 2 U . S . G a l l o n s 
Oil Capacity.      Engine Tank Max. 
1 . 6 4 U . S . G a l l o n s
        MGB Max. 1.93 U.S. Gallons (includes filter)
        TGB Max. 0.13 U.S. Gallons 
Rotor Blades and Control 
Movements. 
For rigging information, refer to the EC 130T2 Maintenance Manual. 
C.G. Range     Longitudinal

15 of 22 H9EU, Rev. 26 
       L a t e r a l 
Datum Longitudinal - 3.4 m (133.8 in) forward of main rotor head
       Lateral - Symmetrical plane of the aircraft 
Leveling Means    Mechanical floor 
Rotor Speeds     In autorotation
       Maximum 430 rpm 
       Minimum 320 rpm 
       I n P o w e r - o n f l i g h t
       375 to 405 RPM 
Rotor Speed Warning Aural at 360 rpm and 410 rpm 
Airspeed Limits    Never exceed speed V NE power on: 
       155 Kt at sea level (depending on long itudinal CG position, See Rotorcraft Flight Manual)
       Never exceed speed V NE power off: 
       125 Kt at sea level 
       S e e R o t o r c r a f t F l i g h t M a n u a l f o r d e c r e a s e  of these values with altitude and temperature. 
Maximum Altitude 23,000 feet pressure altitude 
Serial Numbers    S/ N’s 7355 and subsequent 
DATA PERTINENT TO ALL MODELS EXCEPT EC 130B4 and EC130T2 
Empty Weight CG Range. None 
Datum. Longitudinal :  133.8 in. forward of main rotor hub center. 
Lateral : Vertical plane pa ssing longitudinally through main rotor hub center. 
Leveling Means.     Tr ansmission support platform

16 of 22 H9EU, Rev. 26 
Minimum Crew.     1 pilot 
Maximum Passengers. 5 (1 in front, 4 in rear) 
Option 6 passengers (2 in front, 4 in rear) 
Maximum Baggage.    Ri ght Baggage Compartment :   220 lb. at 125.98 in. 
        Left Baggage Compartment : 264 lb. at 125.98 in. 
        Rear Baggage Compartment : 176 lb. at 181.10 in. 
        Main Cabin (on rear  : 682 lb. at 88.58 in. 
  (on LH fwd. :   330 lb. at   61.02 in. 
350BA included
“ 
“ 
“ 
“ 
Fuel Capacity. Total :   142.7 U.S. Gallons at 136.8 in. 
Usable :   142.3 U.S. Gallons at 136.8 in. (post AMS 07.0289) 
For 350BA version AMS 07.0289 is applied. 
142.1 U.S. Gallons at 136.8 in. (post mod OP-4605) 
        (See NOTE 1 for data on unusable fuel) 
Oil Capacity.      Engine Tank Max. 
1.37 U.S. Gallons at 144.76 in. for AS 350B, AS350BA and AS 350B1 
1.00 U.S. Gallons at 144.76 in. for other models 
        (See NOTE 1 for data on undrainable oil)
        MGB Max. 1.72  U.S. Gallons at 134.4 in. 
        TGB Max. 0.09 U.S. Gallons at 379.5 in. 
Rotor Blades and Control 
Movements. 
For rigging information, refer to the appropriate AS-350 Maintenance Manual. 
Production Basis: Production Certificate No. 343CE. The manufacturer, (Airbus Helicopters Inc. (AHI), 
formerly known as American Eurocopter) is authorized to issue airworthiness certificates 
under 14 CFR 21.183 (a). 
NOTE: These models listed on the Airbus Helicopters Inc. (AHI) Production Limitation 
Record are being produced under Licensing Agreement between Airbus Helicopters (AH) 
and Airbus Helicopters Inc. (AHI), Columbus, Mississippi. 
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. 
Rotorcraft model AS350B2 S/N 3951 and subsequent, may be produced either by 
American Eurocopter in Columbus, Mississippi or Eurocopter France.  Rotorcraft S/N 
7810 and subsequent may be produced by Airbus Helicopters Inc.(AHI) in Columbus, 
Mississippi, or Airbus Helicopters (AH).  Validate manufacturer by viewing the aircraft 
data plate. 
Rotorcraft model AS350B3 S/N 3995 and subsequent, may be produced either by 
American Eurocopter in Columbus, Mississippi or Eurocopter France.  Rotorcraft S/N 
7814 and subsequent may be produced by Airbus Helicopters Inc. (AHI), in Columbus, 
Mississippi, or Airbus Helicopter (AH).  Validate manufacturer by viewing the aircraft 
data plate. 
Certification Basis. 14 CFR 21.29 and part 27 effective February 1, 1965 plus Amendments 27-1 through 27-
10, plus FAA Special Conditions No. 27-79-EU-23, dated August 13, 1977. 
Equivalent safety, in lieu of direct compliance, found with respect 14 CFR 27.1189, 
Shutoff Means. 
Equivalent Safety, in lieu of direct compliance, found with respect to 14 CFR 27.923(b), 
Rotor drive system and control mechanism test for Model 
AS-350B1. 
FAA Special Condition No. 27-001-SC for FADEC HIRF and Equivalent level of Safety 
found with respect to 14 CFR 27.1549(b) for the Model AS350B3.

17 of 22 H9EU, Rev. 26 
EC 130B4 CERTIFICATION BASIS 
EC 130T2 CERTIFICATION BASIS 
For A/C incorporating mod. OP3369 (2370 kg/5225 lb mass extension) the 
following 14 CFR part 27 Amendments 27-1 through 27-40, are replacing the 
same requirement from the certification basis above : 27 §1; §21; §25; §27; §33; 
§45; §51; §65; §71; §73; §75; §79; §141; §143; §173; §175; §177; §241; §301; 
§303; §305; §307; §309; §321; §337; §339; §341; §351; §471; §473; §501; 
§505; §521; §547; §549; §563(b); §571; §602; §661; §663; §695; §723; §725; 
§727; §737; §751; §753; §801(b)(d); §927(c); §1041; §1043; §1045; §1301; 
§1501; §1519; §1529; §1581; §1583; §1585; §1587; §1589. 
For AS350B3 A/C incorporating mod. OP-4605 (installation of a fuel system 
improving crashworthiness), 14 CFR 27.561(c) at Amendment 27-32 replaces the 
same requirement from the certification basis above for the following elements of 
the fuel tank lower structure affected by this modification: cradles, longitudinal 
beams, X-stops and rods. 
For AS350 B3 A/C incorporating modification 07.20034 (AS350 B3 with Crash 
Resistant Fuel System drop test configuration), the following 14 CFR part 27 
Amendments 27-1 through 27-47 are ame nding the same requirement from the 
certification basis above: 
- §863; §901(b)(5); §952; §963(e)(f)(g)(h); §967; §973; §975(b). Applicable for 
the fuel system and airframe structure / fuel system interfaces (see NOTE 16) 
Type Certificate No. H9EU. 
Date of application for Type Certificate: April 6, 1976. 
14 CFR 21.29 and part 27 Amendment 27-1 through Amendment 27-32 except 14 CFR 
27.952 is not adopted. 
14 CFR 36 Appendix H through Amendment 20. 
Special Condition 27-009-SC for HIRF. 
Equivalent Level of Safety Findings 
- 14 CFR 27.1549(b) Powerplant Instrument Markings 
- 14 CFR 27.1027(b)(2) Main Gearbox Oil Filter Bypass 
The French Direction Generale de l’Aviation Civile (DGAC) originally type 
certificated this rotorcraft under its type certificate TC 84.  The FAA validated 
this product under U.S. Type Certificate Number H9EU.  Effective September 
28, 2003, the European Aviation Safety Agency (EASA) began oversight of this 
product on behalf of the DGAC. 
Same as EC130B4 except the following: 
14 CFR 27.952 at amendt 27-30. 
FAR 27.1317 at amendt 42. 
Special Condition 27-028-SC for Use of 30-Minute Power Rating. 
For A/C incorporating modification EC130 T2 New Tailboom (07.4581, 07.4592, 
07.4593, 07.9809), the following 14 CFR Part 27 Amendments 27-1 through 27-
47 are amending the same requirement from the certification basis above:

18 of 22 H9EU, Rev. 26 
Import Requirements. 
SERVICE INFORMATION. 
EQUIPMENT. 
- §351 (rear engine cowling and thermal shield area); 
- §573 (composite spacer, fenestron one-shot); 
§610 (for rear engine compartment and fenestron structure). 
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 H9EU and to be in a 
condition for safe operation.” 
A U.S. Airworthiness Certificate may be issued on the basis of a certificate of 
airworthiness for export signed by a representative of the Centro Tecnico 
Aeroespacial (CTA), the Brazilian civil airworthiness authority which states in 
the English language: 
“The helicopter covered by this certificate has been examined, tested, and found 
to conform to the Type design approved under FAA Type Certificate No. H9EU 
and to be in a condition for safe operation.” 
Major modifications to the imported aircraft must be FAA approved. (see Notes 
10 and 11). 
The AS350C and AS350D1, all serial numbers, are ineligible for import. (see 
Notes 14 and 15.) 
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. 
Service bulletins, structural repair manuals, vendor manuals, AFMs, and 
overhaul and maintenance manuals, which contain a statement that the 
document 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), are accepted by the FAA and are considered FAA 
approved.  These approvals pertain to the design data only. 
The basic required equipment as prescribed in the applicable airworthiness regulations 
(See Certification Basis) must be installed in the helicopter for certification.  Eurocopter 
France Report No. 350A.04.4320 lists required and optional equipment for the helicopter. 
In addition, the following equipment is required: 
DGAC-or EASA approved Rotorcraft Flight Manual identified as Code B, approved as 
follows:

19 of 22 H9EU, Rev. 26 
For Model AS-350B 
For Model AS-350C 
For Model AS-350D 
For Model AS-350D1 
For Model AS-350B1 
For Model AS-350B2 
For Model AS-350BA 
For Model AS-350B3 
:  Approved November 9, 1978. or later approved revisions. 
:  Approved Decem ber 21, 1977, including Rev. No. 2 
  approved December 8, 1978. or later approved revisions. 
 (see NOTE 14) 
:  Approved July 5, 1978. or later approved revisions. 
:  Approved July 4, 1978. or later approved revisions. 
( s e e N O T E 1 5 ) 
:  Approved February 11 , 1987. Rev. 0 plus Rev. 1A and 1B 
  and specific pages marked B or later approved revisions. 
:  Approved June 8, 1990 - Rev. 0 plus Rev. 1 plus Sup 0 Rev.
  2 or later approved revisions. 
:  Approved March 11, 1992. 
:  Approved December 24, 1997, or later approved revisions 
  plus, rapid Revision RR 1A for aircraft equipped with Arriel 
  2B engine or Approved July 16, 2004 for aircraft equipped
  w i t h  A r r i e l  2 B 1  e n g i n e .
  EASA Approved June 17, 2011 + FAA Code B Appendix for 
aircraft equipped with Arriel 2D engine or later approved 
r e v i s i o n s . 
For Model EC 130B4 :  Approved November 29, 2000 plus ITR 1A and ITR 1B dated
  May 17, 2001 (B code not applicable) or later approved  
r e v i s i o n s . 
For Model EC 130T2 :  EASA Approved May 25, 2012 + FAA Code B Appendix 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 certificated empty weight and corresponding center of gravity location must 
include unusable fuel of 20.5 lb., at 136.8 in., and undrainable oil of 1.8 lb., at 171.0 in.  For 
Models AS350B/C/D after embodiment of modification AMS 07.0289 and for Models AS350B1 
and BA, the unusable fuel is 3.1 lb.  For Model AS350B3 after embodiment of modification OP-
4605, the unusable fuel is 4.4 lb. 
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. All placards indicated in the Rotorcraft Flight Manual must be installed in the appropriate location. 
NOTE 3. Information essential to the proper maintenance of the helicopter is contained in the manufacturer’s 
AS-350 Maintenance Manual provided with each helicopter.  Life-limited components and 
associated retirement times are presented in Chapter 5, Section CD 5.99 or MSM chapter 04, and 
must be replaced in accordance therewith. 
NOTE 4. For compliance with applicable powerplant ice protection requirements, the helicopter must be 
equipped during all operations with engine air inlet conforming with Eurocopter France Dwg. No. 
350A58-1607 for aircraft fitted with Turbomeca Arriel engines and with Dwg. No. 350A58-1608 
for aircraft fitted with Lycoming engines. 
NOTE 5. Except for difference in maximum certificated empty weight, the model AS 350D and AS 350D1 
are identical to each other. 
NOTE 6. A.  When operating at maximu m weights above, 4,190 pounds DGAC-approved  
Rotorcraft Flight Manuals, identified as Code B, approved as follows, are required: 
1) 
2) 
for Model AS-350B: 
for Model AS-350C: 
Issue 1, amendment 3, approved May 10, 1979. 
Issue 1, amendment 4, approved May 10, 1979.

20 of 22 H9EU, Rev. 26 
3) for Model AS-350D: Issue 1, amendment 1, approved May 10, 1979. 
B.  For models AS-350B, AS-350C, AS-350D for cargo sling or cargo swing operations the 
maximum weight, including the external load, may be 4,630 pounds provided: 
1) at least 330 pounds of the external load are releasable, and 
2) the rotorcraft is operated in accordance with the appropriate Rotorcraft Flight Manual in 
part A of this note and, 
a)  Eurocopter France Supplement No. 2 to that DGAC-approved Manual, dated 
  May 10, 1979 or later EASA/DGAC approved revision, for the cargo sling, or, 
b)  Eurocopter France Supplement 2A to that DGAC-approved Manual, dated May 18,  
  1979 or later EASA/DGAC approved revision, for the cargo swing. 
C.  For AS 350B1 model for cargo sling or cargo swing operations the maximum 
weight including the external load, may be 5,402 pounds provided: 
1) at least 552 pounds of the external load are releasable, and 
2) the rotorcraft is operated in accordance with the appropriate RFM and 
a)  Eurocopter France supplement 10-1 to that DGAC approved Manual, dated
  January 9, 1986 or later EASA/DGAC approved revision, for the cargo swing or 
b)  Eurocopter France supplement 10-2 to that DGAC approved Manual, dated
  January 9, 1986 or later EASA/DGAC approved revision, for the cargo sling. 
D.  For AS 350B2 model for cargo sling or cargo swing operations the maximum weight including 
the external load, may be 5,512 pounds provided: 
1) at least 551 pounds of the external load are releasable, and 
2) the rotorcraft is operated in accordance with the appropriate RFM and 
a)  Eurocopter Fran ce supplement 11 to that DGAC-approved Manual, dated 
April 26, 1989 or later EASA/DGAC approved revision, for the cargo swing or, 
b)  Eurocopter France supplement 12 to that DGAC approved Manual, dated April 26, 
  1989 or later EASA/DGAC approved revision, for the cargo sling. 
E.   For AS 350BA model for cargo sling or cargo swing operations the maximum weight including 
the external load may be 4961 lb. 
1) at least 331 pounds of the external load are releasable and 
2) the rotorcraft is operated in accordance with the appropriate RFM and 
a)  Eurocopter France supplement 11 to that DGAC approved Manual, dated 
  November 26, 1991 or later EASA/DGAC approved revision, for the cargo swing. 
b)  Eurocopter France supplement 12 to that DGAC approved Manual, dated
  November 26, 1991 or later EASA/DGAC approved revision, for the cargo sling. 
F.  For AS 350B3 model, Arriel2B mounted, for cargo sling or cargo swing operations the 
maximum weight including the external load may be 6173 lb. 
1) at least 1212 pounds of the external load are releasable and 
2) the rotorcraft is operated in accordance with the appropriate RFM and 
a)  Eurocopter France supplement 11 to that DGAC approved Manual, dated 
  December 24, 1997 for the cargo swing or 
b)  Eurocopter France supplement 12 to that DGAC approved Manual, dated
  December 24, 1997 for the cargo sling. 
c)  Eurocopter France supplement 13 to that DGAC approved Manual, dated 
  February 16, 1998 for the cargo swing. 
  For AS 350B3 model, Arriel2B1 mounted, for cargo sling or cargo swing operations the 
maximum weight including the external load may be 6173 lb. 
1) at least 1212 pounds of the external load are releasable and 
2) the rotorcraft is operated in accordance with the appropriate RFM and 
a)  Eurocopter France supplement 12 to that DGAC approved Manual, dated July 16,

21 of 22 H9EU, Rev. 26 
  2004 later EASA/DGAC approved revision for the cargo swing or 
b)  Eurocopter France supplement 13.1 to that DGAC approved Manual, dated July 16, 
  2004 or later EASA/DGAC approved revision for the cargo sling. 
c)  Eurocopter France supplement 13.2 to that DGAC approved Manual, dated Feb 15, 
  2005 or later EASA/DGAC approved revision for the cargo swing. 
  For AS 350B3 model, Arriel2D mounted, for cargo sling or cargo swing operations the 
maximum weight including the external load may be 6173 lb. 
1) at least 1212 pounds of the external load are releasable and 
2) the rotorcraft is operated in accordance with the appropriate RFM and 
a)  Eurocopter France supplement 12 to that EASA approved Manual, dated June 17, 
  2011 later EASA approved revision for the cargo swing or 
b)  Eurocopter France supplement 13.1 to that EASA approved Manual, dated June 17, 
  2011 or later EASA approved revision for the cargo sling. 
c)  Eurocopter France supplement 13.2 to that EASA approved Manual, dated June 17, 
  2011 or later EASA approved revision for the cargo swing. 
NOTE 7.  Emergency fuels: 
For AS 350B3 model, Arriel2B mounted 
A. Use of aviation gasoline MIL-G-5572, Grade 80/87; Grade 110/130 and Grade 115/145 is 
limited to 25 hours maximum within one overhaul period and should have 2% mineral 
lubricating oil added, if possible.  In addition, the use of Grade 115/145 is limited 
operations below 1500 feet pressure altitude. 
C. Use of automotive gasoline MIL-G-3056 is limited to a fuel temperature up to 25°C. 
For AS 350B3 model, Arriel2B1 or Arriel2D mounted 
No emergency fuel 
NOTE 8. For AS 350B, the aural warning sounds when the rotor speed drops below: 
      335 rpm before embodi ment of modification AMS 07.1891 
      360 rpm before embodime nt of modification ASM 07.1891
      For AS350BA, AMS 07.1891 is applied. 
NOTE 9. The model AS350B3, EC 130B4 and EC130T2 rotorcraft employs electronic engine controls, 
commonly named Full authority Digital Engine Controls (FADEC) and is recognized to be more 
susceptible to Electromagnetic Interference (EMI) than rotorcraft that have only manual (non-
electronic) controls. (EMI may be the result of radiated or conducted interference.)  For this reason 
modifications that add or change systems that have the potential for EMI, must either be qualified 
to a standard acceptable to the FAA or  tested at the time of installation for interference to the 
FADEC. This type of testing must employ the particular FADEC’s diagnostic techniques and 
external diagnostic techniques. The test procedure must be FAA approved. 
NOTE 10. Helibras (Brazil) has signed with Eurocopter (France) a technical cooperation agreement contract to 
manufacture in Brazil the AS 350 BA, AS 350 B2 and AS 350 B3 models using kits produced by 
Eurocopter, in conformity to the DGAC France approved Type design.  Helibras helicopters are 
produced under the Helibras Production Certificate, assembled and tested in accordance with 
procedures approved under the French Type design by Eurocopter and accepted by the Centro 
Tecnico Aeroespacial (CTA) under the terms and conditions of the Helibras Production Certificate. 
Helicopter serial numbers produced by Helibras as the manufacturer are identified in Eurocopter 
document number L102 001, entitled “List of serial numbers of stage 2 helicopters produced by 
Helibras” referenced in both the French and the Brazilian Type Certificate Data Sheets (See Import 
Requirements). 
NOTE 11. Helicopters with a model prefix of “HB” as in “HB 350 B” are not eligible for airworthiness 
certification in the U.S.

22 of 22 H9EU, Rev. 26 
NOTE 12. Effective January 1, 2014, Eurocopter France name was changed to Airbus Helicopters. 
NOTE 13. The AS350B3 model helicopter which type design incorporates the Arriel 2D engine installation 
has the commercial designation AS350B3e. 
NOTE 14. Model AS350C helicopters are ineligible for U.S. certificate of airworthiness due to Airbus 
Helicopters surrendering the type design, and EASA subsequently cancelling it on June 01, 1997. 
NOTE 15. Model AS350D1 helicopters are ineligible for U.S. certificate of airworthiness due to Airbus 
Helicopters surrendering the type design, and EASA subsequently cancelling it on December 14, 
2000. 
NOTE 16. Title 49 U.S.C. Section 44737 Requires that new-production of old-designed rotorcraft are 
compliant with the requirements of paragraphs (1), (2), (3), (5), and (6) of 14 CFR §27.952(a), 
§27.952(c), §27.952(f), §27.952(g), §27.963(g) (but allowing for a minimum puncture force of 250 
pounds if successfully drop tested in-structure), and §27.975(b). or employ other means acceptable 
to the Administrator to provide an equivalent level of fuel system crash resistance. 
......END.....
```

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- [AD 2022-05-02](https://openairdocs.org/ad/2022-05-02): Engine Fuel Control/Turbine Engines · Airbus Helicopters AS350B3 and EC130T2. Effective Mar 30, 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 2022-02-04](https://openairdocs.org/ad/2022-02-04): Hydraulic Power System Wiring · Airbus Helicopters AS350B, AS350B2, AS350B3 and 1 more. Effective Feb 25, 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 2021-19-09](https://openairdocs.org/ad/2021-19-09): Cabin Equipment/Furnishings · Airbus Helicopters AS355E, AS355F, AS355F1 and 6 more. Effective Nov 4, 2021
- [AD 2021-19-02](https://openairdocs.org/ad/2021-19-02): Rotorcraft flight control · Airbus Helicopters EC130B4 and EC130T2. Effective Nov 1, 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 2021-10-25](https://openairdocs.org/ad/2021-10-25): Tail rotor blades · Airbus Helicopters EC130B4 and EC130T2. Effective Jul 6, 2021
- [AD 2021-09-05](https://openairdocs.org/ad/2021-09-05): Rotorcraft Tail Boom · Airbus Helicopters EC130B4 and EC130T2. Effective Jun 2, 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 2021-04-08](https://openairdocs.org/ad/2021-04-08): Engine Control System Wiring · Airbus Helicopters AS350B3. Effective Apr 1, 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 2020-25-11](https://openairdocs.org/ad/2020-25-11): Doors · Airbus Helicopters EC120B and EC130B4. Effective Jan 21, 2021
- [AD 2020-23-09](https://openairdocs.org/ad/2020-23-09): Doors · Airbus Helicopters EC130B4. Effective Dec 24, 2020
- [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 2020-20-03](https://openairdocs.org/ad/2020-20-03): Main Rotor Drive Indicating System · Airbus Helicopters AS350B2. Effective Nov 3, 2020

All 191: https://openairdocs.org/tcds/H9EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Airbus Helicopters AS350B3](https://openairdocs.org/model/airbus-helicopters-as350b3): 291 aircraft (registry code 1145005)
- [Eurocopter AS 350 B3](https://openairdocs.org/model/eurocopter-as-350-b3): 167 aircraft (registry code 8680954)
- [Eurocopter EC 130 B4](https://openairdocs.org/model/eurocopter-ec-130-b4): 154 aircraft (registry code 8680989)
- [Eurocopter AS 350 B2](https://openairdocs.org/model/eurocopter-as-350-b2): 146 aircraft (registry code 8680950)
- [Airbus Helicopters EC 130 T2](https://openairdocs.org/model/airbus-helicopters-ec-130-t2): 124 aircraft (registry code 1145302)
- [American Eurocopter AS350B3](https://openairdocs.org/model/american-eurocopter-as350b3): 124 aircraft (registry codes 1145004, 1145002)
- [Airbus Helicopters AS 350B3](https://openairdocs.org/model/airbus-helicopters-as-350b3): 56 aircraft (registry code 868096A)
- [American Eurocopter AS350B2](https://openairdocs.org/model/american-eurocopter-as350b2): 38 aircraft (registry codes 1145100, 1145000)
- [Eurocopter EC 130 T2](https://openairdocs.org/model/eurocopter-ec-130-t2): 22 aircraft (registry code 868099A)
- [Aerospatiale AS350 B2 ECUREUIL](https://openairdocs.org/model/aerospatiale-as350-b2-ecureuil): 21 aircraft (registry code 8680813)
- [Aerospatiale AS350BA](https://openairdocs.org/model/aerospatiale-as350ba): 18 aircraft (registry code 8680817)
- [Aerospatiale AS350B](https://openairdocs.org/model/aerospatiale-as350b): 13 aircraft (registry code 8680800)
- [Eurocopter AS 350 B2 ECUREUIL](https://openairdocs.org/model/eurocopter-as-350-b2-ecureuil): 13 aircraft (registry code 8680951)
- [Eurocopter AS 350 BA](https://openairdocs.org/model/eurocopter-as-350-ba): 13 aircraft (registry code 8680955)
- [Aerospatiale AS350B2](https://openairdocs.org/model/aerospatiale-as350b2): 11 aircraft (registry code 8680877)
- [Airbus Helicopters AS350B2](https://openairdocs.org/model/airbus-helicopters-as350b2): 10 aircraft (registry code 1145102)
- [Eurocopter France AS 350 B3](https://openairdocs.org/model/eurocopter-france-as-350-b3): 8 aircraft (registry code 8680963)
- [Eurocopter France AS350B2](https://openairdocs.org/model/eurocopter-france-as350b2): 8 aircraft (registry code 8680973)
- [Eurocopter France EC 130 B4](https://openairdocs.org/model/eurocopter-france-ec-130-b4): 6 aircraft (registry code 8680996)
- [Airbus Helicopters AS350B3E](https://openairdocs.org/model/airbus-helicopters-as350b3e): 5 aircraft (registry code 1155005)
- [S N I A S AS-350B ECUREUIL](https://openairdocs.org/model/s-n-i-a-s-as-350b-ecureuil): 5 aircraft (registry code 8680801)
- [Aerospatiale AS350B1 ECUREUIL](https://openairdocs.org/model/aerospatiale-as350b1-ecureuil): 2 aircraft (registry code 8680811)
- [Airbus Helicopters AS350BA](https://openairdocs.org/model/airbus-helicopters-as350ba): 2 aircraft (registry code 8680766)
- [Airbus Helicopters EC 130B4](https://openairdocs.org/model/airbus-helicopters-ec-130b4): 2 aircraft (registry code 8680150)
- [Eurocopter EC 130](https://openairdocs.org/model/eurocopter-ec-130): 2 aircraft (registry code 8680988)
- [Eurocopter France AS350BA](https://openairdocs.org/model/eurocopter-france-as350ba): 2 aircraft (registry code 868097A)
- [Eurocopter AS 350 B3E](https://openairdocs.org/model/eurocopter-as-350-b3e): 1 aircraft (registry code 868095B)
- [Eurocopter AS350B](https://openairdocs.org/model/eurocopter-as350b): 1 aircraft (registry code 8680942)
- [Eurocopter ECUREUIL AS 350 B](https://openairdocs.org/model/eurocopter-ecureuil-as-350-b): 1 aircraft (registry code 8680969)
- [Eurocopter France AS350B](https://openairdocs.org/model/eurocopter-france-as350b): 1 aircraft (registry code 8680961)
- [S N I A S AS350BA](https://openairdocs.org/model/s-n-i-a-s-as350ba): 1 aircraft (registry code 8680957)
- [S N I A S AS350D ASTAR](https://openairdocs.org/model/s-n-i-a-s-as350d-astar): 1 aircraft (registry code 8680803)
- [Aerospatiale AS350B ECUREUIL](https://openairdocs.org/model/aerospatiale-as350b-ecureuil): 0 aircraft (registry code 8680819)
- [Aerospatiale AS350D](https://openairdocs.org/model/aerospatiale-as350d): 0 aircraft (registry code 8680804)
- [Eurocopter AS350-B-1](https://openairdocs.org/model/eurocopter-as350-b-1): 0 aircraft (registry code 8680967)
- [Helibras AS 350 B3](https://openairdocs.org/model/helibras-as-350-b3): 0 aircraft (registry code 868096B)
- [Helibras AS-350B2](https://openairdocs.org/model/helibras-as-350b2): 0 aircraft (registry code 8680959)
- [S N I A S AS-350B2](https://openairdocs.org/model/s-n-i-a-s-as-350b2): 0 aircraft (registry code 8680799)
- [S N I A S AS-350C ASTAR](https://openairdocs.org/model/s-n-i-a-s-as-350c-astar): 0 aircraft (registry code 8680802)
- [S N I A S AS350B1 ECUREUIL](https://openairdocs.org/model/s-n-i-a-s-as350b1-ecureuil): 0 aircraft (registry code 8680956)

## STCs approved under this data sheet (764, first 50)

- [STC SR00653NY](https://openairdocs.org/stc/SR00653NY): nstallation and configuration of Maintenance Step on Transmission Deck Cowling. Airbus Helicopters Canada Limited
- [STC SH8154SW-D](https://openairdocs.org/stc/SH8154SW-D): Installation of a steerable landing light.. Airbus Helicopters Inc.
- [STC SR00643DE](https://openairdocs.org/stc/SR00643DE): Installation of a vapor cycle cabin airconditioning system. Air Comm Corporation
- [STC SR12433IB](https://openairdocs.org/stc/SR12433IB): Fabrication of equipment must be in accordance with the applicable Manufacturing Procedure document as shown on the attached FAA AML No. SR12433IB.. Lake Central Air Services
- [STC SR09502RC](https://openairdocs.org/stc/SR09502RC): Installation of Air Methods Corporation Emergency Medical System and Avionics Package. Air Methods LLC
- [STC SR12419IB](https://openairdocs.org/stc/SR12419IB): Installation of a cockpit floor window P/N 53001002750. KAELIN AIRCRAFTSTRUCTURE GmbH
- [STC SR09496RC-D](https://openairdocs.org/stc/SR09496RC-D): Installation of Trakka Corporation A800 Searchlight System. Airbus Helicopters Inc.
- [STC SR12374IB](https://openairdocs.org/stc/SR12374IB): Installation of the Modular Instrument Panel. XL Aero Inc.
- [STC SR11321DS](https://openairdocs.org/stc/SR11321DS): Installation of a Technisonic TDFM-9300 Multi-band FM Transceiver. Airbus Helicopters Inc.
- [STC SH4716NM](https://openairdocs.org/stc/SH4716NM): Redesign and relocation of cargo door hinges and relocation of cargo door latch. Turbolyft USA Corporation
- [STC SH4791NM](https://openairdocs.org/stc/SH4791NM): Installation of a Geneva Aviation Starter Generator,. Turbolyft USA Corporation
- [STC SH4929NM](https://openairdocs.org/stc/SH4929NM): Installation of high-volume air blower assembly.. Turbolyft USA Corporation
- [STC SH4983NM](https://openairdocs.org/stc/SH4983NM): Installation of 2nd oil cooler.. Turbolyft USA Corporation
- [STC SH5187NM](https://openairdocs.org/stc/SH5187NM): Installation of a video system.. 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 SR00222SE](https://openairdocs.org/stc/SR00222SE): Installation of a supplemental avionics console between the front seats.. 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 SR00388SE](https://openairdocs.org/stc/SR00388SE): Fabrication and Installation of a rear communication console. 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 SR00407NY](https://openairdocs.org/stc/SR00407NY): Installation of litter kit fixed provisions P/N 350-200034-01 or 350-200034-02, and detachable provisions P/N 350-200034-03.. Airbus Helicopters Canada Limited
- [STC SH4747NM](https://openairdocs.org/stc/SH4747NM): Fabrication and Installation of Electrical System Upgrade. AEM USA 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 SR11323DS](https://openairdocs.org/stc/SR11323DS): Installation of RT-7000 RMR Tactical Radio. Airbus Helicopters Inc.
- [STC SR03029NY](https://openairdocs.org/stc/SR03029NY): The installation of a SkyTrac ISAT-200 Airborne Position/Data Communicator upgrade. SkyTrac Systems Ltd.
- [STC SR11332DS](https://openairdocs.org/stc/SR11332DS): Installation of 2nd Garmin GDU 1060 Display and optional L3 ESI-500. Airbus Helicopters Inc.
- [STC SR12293NY](https://openairdocs.org/stc/SR12293NY): Installation of a FreeFlight Systems RA-4500 MKII 5G Tolerant Radar Altimeter. FreeFlight Systems Ltd.
- [STC SR11330DS](https://openairdocs.org/stc/SR11330DS): Installation of a Jupiter Audio System. Airbus Helicopters Inc.
- [STC SR11808LA](https://openairdocs.org/stc/SR11808LA): Installation of tail rotor assemblies, P/N 350TR1000-101/301. Van Horn Aviation LLC
- [STC SR11196DS](https://openairdocs.org/stc/SR11196DS): Installation of GDL 69AH XM Radio and Weather Satellite Data Link. Airbus Helicopters Inc.
- [STC SR11327DS](https://openairdocs.org/stc/SR11327DS): Installation of a KN63 DME with GAD 43e Adapter. Airbus Helicopters Inc.
- [STC SR12178IB](https://openairdocs.org/stc/SR12178IB): Installation of Oil Pressure Sensor part number MPN 2010-0078-10. HELIBRAS - Helicópteros do Brasil S. A.
- [STC SR12146IB](https://openairdocs.org/stc/SR12146IB): Installation of an AEM MTP136D Panel Mount FM Transceiver. Anodyne Electronics Manufacturing Corporation
- [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 SH4343SW-D](https://openairdocs.org/stc/SH4343SW-D): Installation of strobe anti-collision light installation and/or supplemental strobe light. Airbus Helicopters Inc.
- [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 SR11944WI](https://openairdocs.org/stc/SR11944WI): Installation of a Garmin GFC 600H Helicopter Flight Control System. Garmin International Inc.
- [STC SR09510RC](https://openairdocs.org/stc/SR09510RC): Installation of AEM 600W Loud Hailer System. Airbus Helicopters Inc.
- [STC SR03526NY](https://openairdocs.org/stc/SR03526NY): Installation and Configuration of Electrical Power Supply for Optional 50Amp / Longline / Carousel Systems. Airbus Helicopters Canada Limited
- [STC SR12020IB](https://openairdocs.org/stc/SR12020IB): Installation of External Mirror System 350P025 on Right Hand Side (RHS) and/or Left Hand
Side (LHS). BOGGI AERONAUTICS S.R.L.
- [STC SH4016SW-D](https://openairdocs.org/stc/SH4016SW-D): Installation of Hourmeter.. Airbus Helicopters Inc.
- [STC SR11864DE](https://openairdocs.org/stc/SR11864DE): Installation of Belt Driven Auxiliary Generator i. RSG AeroDesign LLC
- [STC SR00115IB](https://openairdocs.org/stc/SR00115IB): Installation of the Advanced Lithium Ion Battery Replacement of Ni-Cad Battery. Vertical Flight Solutions Inc.

All 764: https://openairdocs.org/tcds/H9EU/stcs.md

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.