TYPE CERTIFICATE DATA SHEET Nº ER-8812

ER-8812-23
Type Certificate Holder: (See Note 9) Sheet 01
AIRBUS HELICOPTERS
Aeroport International Marseille-Provence AIRBUS
13725 Marignane cedex HELICOPTERS
FRANCE
AS 350 B1, AS 350 B2,
(Formerly EUROCOPTER) AS 350 BA, AS 350 B3
EC 130 B4, EC 130 T2

05 September 2024

This data sheet, which is part of Type Certificate No. 8812, prescribes conditions and limitations under
which the product, for which the Type Certificate was issued, meets the airworthiness requirements of
the Brazilian Aeronautical Regulations.

I - Model AS 350 B1 (Normal Category), approved 08 November 1988.

ENGINE Turbomeca Arriel 1D (See TCDS nº EM-8012).

FUEL Jet A, Jet A-1, Jet B, JP-5 or JP-8. (See RFM for emergency fuels)

INSTALLED ENGINE LIMITS Minimum Generator

Power Limit Torque T4
Guaranteed Speed
Rating on Shaft Temperature
Power* (NG)**
Maximum
105.5%
Transient --- --- ---
(54649 rpm)
(5 sec.)
Maximum at 100.8
510 kw
Takeoff 830 N.m +0.4/-0 % 845ºC
(684 hp)
(5 min.) (52214 rpm)
Maximum 450 kw 98%
830 N.m 795ºC
Continuous (603 hp) (50764 rpm)
* ISA, ground level.
** 100% = 51800 rpm.

ROTOR SPEED LIMITS Power-on flight: 390 +4 / -5 rpm

In autorotation: Maximum 430 rpm
Minimum 320 rpm (audio warning below 365 rpm)
TRANSMISSION TORQUE Maximum Torque
LIMITS IAS 74 km/h
94 %
(40 kt) or higher:
IAS below
100 %
74 km/h (40 kt):
100% torque = 488 kW power output at 394 rpm main rotor speed or 478
kW at 386 rpm

OIL Refer to Flight Manual.

AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 2/20

AIRSPEED LIMITS (IAS) Power-on Never Exceed Speed (VNE)

Absolute VNE: 287 km/h (155 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
In cold weather: Subtract the following value from the above VNE
• 19 km/h (10 kt) when OAT is below -30°C
Power-off Never Exceed Speed (VNE)
Absolute VNE: 231km/h (125 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
In cold weather: Subtract the following value from the above VNE
• 19 km/h (10 kt) when OAT is between -20°C and
-30°C
• 37 km/h (20 kt) when OAT is below -30°C,
without VNE being less than 120 km/h (65 kt)

CG RANGE Longitudinal:
Forward (m) Rear (m) Gross Weight (kg)
3.17 3.50 1200 and below
3.17 3444 2000
3.20 3.43 2200
Straight line variation between points given
Lateral (See Note 5):
- Left of CL: 0.18 m
- Right of CL: 0.14 m

MAXIMUM WEIGHT 2200 kg (4850 lb).

MINIMUM CREW 1 pilot in the right side.

NUMBER OF SEATS 6 maximum (pilot included)

When the aircraft is fitted with the two-place seat optional equipment, the
number of seats is increased to seven (pilot included). This optional is to
be used in accordance with the corresponding Flight Manual Supplement.

FUEL CAPACITY Total: 540 liters

Usable fuel: 538.75 liters
Unusable fuel: 1.25 liters

OIL CAPACITY Engine: 5.2 liters

MGB: 6.5 liters
TGB: 0.33 liters

MAXIMUM OPERATING 6096 m (20000 ft) en route

ALTITUDE 4267 m (14000 ft) for takeoff and landing

S/N’s ELIGIBLE 1822 and subsequent.

A Certificate of Airworthiness for Export endorsed as noted under "Import
Requirements" must be submitted for each individual aircraft for which
application for a Brazilian Certificate of Airworthiness is made.
Aircraft manufactured in Brazil: see Note 7.
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 3/20

II - Model AS 350 B2 (Normal Category), approved 06 November 1990.

ENGINE Turbomeca Arriel 1D1 (See TCDS EM-8012).
FUEL Jet A, Jet A1, Jet B, JP1, JP4, JP5, JP8, F34, F35, F43, F44 or F40. (See
RFM for emergency fuels)

INSTALLED ENGINE LIMITS B2 without B2 with

VEMD VEMD
Limit Minimum
Power Generator Generator T4
Torque Guaranteed
Rating Speed Speed Temp.
on Shaft Power*
(NG)** (NG)**
(Ng) (Ng)
Maximum
107.5% (+6) 103.1% (+1)
Transient --- --- ---
(55685 rpm) (53406 rpm)
(5 sec.)
Without P2
Maximum Automatic
478 kw*** air bleed (0)
at Takeoff 830 N.m P2 derating 845ºC
(641 hp) With P2 air
(5 min.) by VEMD
bleed (-0.6)
Maximum 449 kw 98% (-3.5) 98% (-4)
830 N.m 795ºC
Continuous (602 hp) (50764 rpm) (50764 rpm)
* ISA, ground level.
** 100% = 51800 rpm.
*** The mechanical power has been limited to this value taking the fuel
flow limit into account.

ROTOR SPEED LIMITS Power-on flight: 390 +4 / -5 rpm

In autorotation: Maximum 430 rpm (audio warning above 410 rpm)
Minimum 320 rpm (audio warning below 360 rpm)
TRANSMISSION TORQUE Maximum
LIMITS 94 %
continuous
Takeoff range
from 0 to 94 to 100 %
74 km/h (40 kt)
Max. takeoff
100 %
torque
Max. transient (5s) 107 %
100% torque = 478 (641 shp) at 386 rpm main rotor speed

OIL Refer to Flight Manual.

AIRSPEED LIMITS (IAS) Power-on Never Exceed Speed (VNE)

Absolute VNE: 287 km/h (155 kt) for HP=0

In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
In cold weather: Subtract the following value from the above VNE
• 19 km/h (10 kt) when OAT is below -30°C
Power-off Never Exceed Speed (VNE)
Absolute VNE: 231km/h (125 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
In cold weather: Subtract the following value from the above VNE
• 19 km/h (10 kt) when OAT is between -20°C and
-30°C
• 37 km/h (20 kt) when OAT is below -30°C,
without VNE being less than 120 km/h (65 kt)
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 4/20

CG RANGE Lateral (See Note 5):

- Left of CL: 0.18 m

- Right of CL: 0.14 m

Longitudinal:

MAXIMUM WEIGHT 2 250 kg (4 960 lb ).

MINIMUM FLIGHT CREW 1 pilot in the right side.

NUMBER OF SEATS 6 maximum (pilot included)

When the aircraft is fitted with the two-place seat optional equipment, the
number of seats is increased to seven (pilot included). This optional is to
be used in accordance with the corresponding Flight Manual Supplement.

FUEL CAPACITY Total: 540 liters (142.70 US gal)

Usable fuel: 538.75 liters (142.34 US gal)
Unusable fuel: 1.25 liters (0.33 US gal)

OIL CAPACITY Engine: 5.2 liters (1.37 US gal)

MGB: 6.5 liters (1.72 US gal)
TGB: 0.33 liters (0.09 US gal)

MAXIMUM OPERATING 6096 m (20 000 ft)

ALTITUDE Refer to Flight Manual for Takeoff and landing

S/N’s ELIGIBLE 2100 and subsequent.

Imported aircraft:
A Certificate of Airworthiness for Export endorsed as noted under "Import
Requirements" must be submitted for each individual aircraft for which
application for a Brazilian Certificate of Airworthiness is made.
Aircraft manufactured in Brazil: see Note 7.

II - Model AS 350 BA (Normal Category), approved 22 July 1992.

AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 5/20

ENGINE Turbomeca Arriel 1B (See TCDS nº EM-8012).

FUEL Jet A, Jet A-1, Jet B or JP-4. (See RFM for emergency fuels)

INSTALLED ENGINE LIMITS Minimum

Generator T4
Power Rating Guarantide
Speed (NG)** Temperature
Power*
Maximum
105%
Transient --- ---
(54390 rpm)
(5 sec.)
Maximum at
478 kw 100 %
Takeoff 810ºC
(641hp) (51800 rpm)
(5 min.)
Maximum 440 kw 98 %
775ºC
Continuous (590 hp) 50764 rpm
Maximum T4 starting: 840°C.
* ISA, ground level.
** 100% = 51800 rpm.

ROTOR SPEED LIMITS Power-on flight: 390 +4 / -5 rpm

In autorotation: Maximum 430 rpm (audio warning above 410 rpm)
Minimum 320 rpm (audio warning below 360 rpm)
TRANSMISSION TORQUE Maximum Torque
LIMITS IAS 74 km/h
83 %
(40 kt) or higher:
IAS below
88 %
74 km/h (40 kt):
100% torque = 478 kW at 386 rpm main rotor speed

OIL Refer to Flight Manual.

AIRSPEED LIMITS (IAS) Power-on Never Exceed Speed (VNE)

Absolute VNE: 287 km/h (155 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
In cold weather: Subtract the following value from the above VNE
• 19 km/h (10 kt) when OAT is below -30°C
Power-off Never Exceed Speed (VNE)
Absolute VNE: 231km/h (125 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
In cold weather: Subtract the following value from the above VNE
• 19 km/h (10 kt) when OAT is between -20°C and
-30°C
• 37 km/h (20 kt) when OAT is below -30°C,
without VNE being less than 120 km/h (65 kt)

CG RANGE Lateral (See Note 5):

- Left of CL: 0.18 m
- Right of CL: 0.14 m

Longitudinal:
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 6/20

MAXIMUM WEIGHT 2 100 kg (4 630 lb)

MINIMUM CREW 1 pilot in the RH seat.

NUMBER OF SEATS 6 maximum (pilot included)

When the aircraft is fitted with the two-place seat optional equipment, the
number of seats is increased to seven (pilot included). This optional is to
be used in accordance with the corresponding Flight Manual Supplement.

FUEL CAPACITY Total: 540 liters

Usable fuel: 538.75 liters
Unusable fuel: 1.25 liters

OIL CAPACITY Engine: 5.2 liters

MGB: 6.5 liters
TGB: 0.33 liters

MAXIMUM OPERATING 4 875 m (16 000 ft)

ALTITUDE Refer to Flight Manual for Takeoff and landing

S/N’s ELIGIBLE 2588 and subsequent.

Imported aircraft:
A Certificate of Airworthiness for Export endorsed as noted under "Import
Requirements" must be submitted for each individual aircraft for which
application for a Brazilian Certificate of Airworthiness is made.
Aircraft manufactured in Brazil: see Note 7.

IV - Model AS-350B3 (Normal Category), approved 15 September 1998. (See Note 8)

ENGINES Turbomeca Arriel 2B or 2B1 or 2D (See TCDS nº EM-9802).

FUEL Jet A, Jet A-1, JP-5 or JP-8. (See RFM for emergency fuels)
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 7/20

INSTALLED ENGINE LIMITS For Arriel 2B (before modifications AMS 072803 and 072808):
Minimum Generator
Power Limit Torque T4
Guaranteed Speed
Rating on Shaft Temperature
Power* NG** (Ng)
Maximum
102.3% (+1)
Transient --- --- ---
(53308 rpm)
(5 sec.)
Maximum at
535 kw 101.1 % (0)
Takeoff 853 N.m 915ºC
(717 hp) (52683 rpm)
(5 min.)
For Vi  70kt
94.8 % (-4)
Maximum 450 kw 49400 rpm
716 N.m 849ºC
Continuous (603 hp) For Vi  70kt
97.1 % (-4)
(50599 rpm)
* ISA, ground level at rotor speed 386 rpm.
** 100% = 52110 rpm – without electrical bleed, nor P2, ISA, ground
level.

For Arriel 2B (after modifications AMS 072803 and 072808) and 2B1:
Minimum Generator
Power Limit Torque T4
Guaranteed Speed
Rating on Shaft Temperature
Power* NG** (Ng)
Maximum
102.3% (+1)
Transient --- --- ---
(53308 rpm)
(5 sec.)
Maximum at
535 kw 101.1 % (0)
Takeoff 853 N.m 915ºC
(717 hp) (52683 rpm)
(5 min.)
Maximum 497 kw 97.1 % (-4)
791 N.m 849ºC
Continuous (666 hp) (50599 rpm)
* ISA, ground level at rotor speed 386 rpm.
** 100% = 52110 rpm – without electrical bleed, nor P2, ISA, ground
level.

For Arriel 2D****

Generator
Minimum
Power Limit Torque Speed T4
Guaranteed
Rating on Shaft Ng*** Temperature
Power*
(NG)**
Maximum
+1 (101.9 %)
Transient --- --- ---
(53100 rpm)
(5 sec.)
Maximum at
535 kw 0 (100.9 %)
Takeoff 853 N.m 949ºC
(717 hp) (52579 rpm)
(5 min.)
Maximum at
Takeoff 535 kw 0 (100.9 %)
853 N.m 949ºC
(30 min.) (717 hp) (52579 rpm)
(HIP)*****
Maximum 497 kw -4 (98.0 %)
791 N.m 905ºC
Continuous (666 hp) (51067 rpm)
* ISA, ground level at rotor speed 386 rpm.
** 100% = 52110.
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 8/20

INSTALLED ENGINE LIMITS *** As the actual limitations depend on ambient conditions, the
(cont.) operational limitations are the Mg values. Ng values correspond to the
maximum Ng reached in the whole flight domain.
**** Note: The engine is not physically derated but its performance is
limited when installed in the AS350B3. Specific limitations have been
implemented in the VEMD, allowing the pilot to control the installed Arriel
2D at the same power limitations as when an Arriel 2B1 is installed, for
each aircraft rating (MCP, MTOP and MTP).
***** Use of HIP (Hover Increased Power, TOP 30 min) is allowed when
enhanced thermal protection is fitted on the AS350B3 tail boom
(modification OP-4309).

ROTOR SPEED LIMITS For AS350B3 Arriel 2B:

Power-on flight: 390 +4 / -5 rpm
For AS350B3 Arriel 2B1:
Power-on flight: 375 to 405 rpm
For AS350B3 Arriel 2D:
Power-on flight: 375 to 405 rpm
For AS350B3 all engines:
In autorotation: Maximum 430 rpm (audio warning above 410 rpm)
Minimum 320 rpm (audio warning below 360 rpm)

TRANSMISSION TORQUE On AS350B3 Arriel 2B (before modifications AMS 072803 and 072808)
LIMITS IAS lower than Max. transient (10s) 104 %
74 km/h (40 kt) Max. continuous 100 %
IAS ≥ 74 km/h
Max. continuous 84 %
(40 kt)
On AS350B3 Arriel 2B (after modifications AMS 072803 and 072808)
IAS lower than Max. transient (10s) 104 %
74 km/h (40 kt) Max. continuous 100 %
IAS ≥ 74 km/h
Max. continuous 92.7 %
(40 kt)
On AS350B3 Arriel 2B1
Max. continuous 92.7 %
Takeoff range
from 0 to 92.7 to 100 %
74 km/h (40 kt)
Max. takeoff 100 %
Max. transient (5s) 104 %
On AS350B3 Arriel 2D
Max. continuous 92.7 %
Takeoff range
from 0 to 92.7 to 100 %
74 km/h (40 kt)
Max. takeoff 100 %
Max. transient (5s) 104 %
100% torque = 535 kW at 386 rpm main rotor speed

OIL Refer to Flight Manual

AIRSPEED LIMITS (IAS) For Arriel 2B (before modifications AMS 072803 and 072808) and 2B1:
Power-on Never Exceed Speed (VNE)
Absolute VNE: 287 km/h (155 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
In cold weather: Subtract the following value from the above VNE
• 19 km/h (10 kt) when OAT is below -30°C
Power-off Never Exceed Speed (VNE)
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 9/20

Absolute VNE: 231km/h (125 kt) for HP=0

In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft), without VNE being less than 120 km/h (65 kt)
In cold weather: Subtract the following value from the above VNE
OIL
• 37 km/h (20 kt) when OAT is below -20°C,
AIRSPEED LIMITS (IAS)
(cont.) without VNE being less than 120 km/h (65 kt)

For Arriel 2B (after modifications AMS 072803 and 072808):

Power-on Never Exceed Speed (VNE)
Absolute VNE: 287 km/h (155 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
In cold weather: Subtract the following value from the above VNE
• 19 km/h (10 kt) when OAT is below -30°C
In the cross- Limited to 246 km/h (133 kt) or the VNE defined above
hatched area in the (the lowest value)
C.G. graph
Power-off Never Exceed Speed (VNE)
Absolute VNE: 231km/h (125 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft) , without VNE being less than 120 km/h (65
kt)
In cold weather: Subtract the following value from the above VNE
• 37 km/h (20 kt) when OAT is below -20°C,
without VNE being less than 120 km/h (65 kt)
For Arriel 2D****
Power-on Never Exceed Speed (VNE)
Absolute VNE: 287 km/h (155 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
In cold weather: Subtract the following value from the above VNE
• 19 km/h (10 kt) when OAT is below -30°C
Power-off Never Exceed Speed (VNE)
Absolute VNE: 231km/h (125 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft), without VNE being less than 120 km/h (65 kt)
In cold weather: Subtract the following value from the above VNE
• 37 km/h (20 kt) when OAT is below -20°C,
without VNE being less than 120 km/h (65 kt)

CG RANGE Lateral (See Note 5):

- Left of CL: 0.18 m up to 2250 kg
0.08 m from 2250 kg up to 2370 kg for aircraft
incorporating mod. OP-3369
- Right of CL: 0.14 m up to 2250 kg
0.08 m from 2250 kg up to 2370 kg for aircraft
incorporating mod. OP-3369
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 10/20

Longitudinal:
For AS350B3 Arriel 2B1 aircraft incorporating mod. OP-3369:

For AS350B3 Arriel 2B (before modifications AMS 072803 and 072808)

and AS350B3 Arriel 2B1:
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 11/20

For AS350B3 Arriel 2B (after modifications AMS 072803 and 072808):

For AS350B3 Arriel 2D aircraft incorporating mod. OP-3369:

For AS350B3 Arriel 2D:

AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 12/20

MAXIMUM WEIGHT 2250 kg (4960 lb)

2370 kg (5224 lb) for aircraft incorporating mod. OP-3369.

MINIMUM CREW 1 pilot in the right side.

NUMBER OF SEATS 6 maximum (pilot included)

When the aircraft is fitted with the two-place seat optional equipment, the
number of seats is increased to seven (pilot included). This optional is to
be used in accordance with the corresponding Flight Manual Supplement.

FUEL CAPACITY Total: 540 liters

Usable fuel: 538.75 liters
Unusable fuel: 1.25 liters

OIL CAPACITY Engine: 5.2 liters

MGB: 6.5 liters
TGB: 0.33 liters

MAXIMUM OPERATING 7 010 m (23 000 ft)

ALTITUDE
S/N’s ELIGIBLE 3063 and subsequent.
Imported aircraft:
A Certificate of Airworthiness for Export endorsed as noted under "Import
Requirements" must be submitted for each individual aircraft for which
application for a Brazilian Certificate of Airworthiness is made.
Aircraft manufactured in Brazil: see Note 7.

V - Model EC 130B4 (Normal Category), approved 14 November 2002.

ENGINES Turbomeca Arriel 2B1 (See TCDS nº EM-9802).

FUEL See Rotorcraft Flight Manual for fuel and additive specification.

INSTALLED ENGINE LIMITS Gas Generator Exhaust Gas

Power Rating
Speed (NG)* (Ng) Temperature (T4)**
Max. transient 102.3% (+1)
865°C (10s)
(53 308 rpm)
Max. take-off (5 min) 101.1% (0)
915°C
(52 683 rpm)
Max. continuous 97.1% (-4)
849°C
(50 598 rpm)
* 100%: 52110 rpm
** Max Continuous during starting: 750°C

ROTOR SPEED LIMITS Power on: 375 to 405 rpm

Power off: Maximum 430 rpm (audio warning ≥ 410 rpm)
Minimum 320 rpm (audio warning = 360 rpm)

TRANSMISSION TORQUE Max. transient (5 s) 104 %

LIMITS Max. take-off: 100 %
Max. continuous: 92.7 %
100% torque = 536 kW at 6000 rpm engine speed = 386 rpm main rotor
speed

OIL Refer to Flight Manual for approved engine and gearbox oils.
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 13/20

AIRSPEED LIMITS (IAS) Power-on Never Exceed Speed (VNE)

Absolute VNE: 287 km/h (155 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
Power-off Never Exceed Speed (VNE)
Absolute VNE: 231 km/h (125 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)

CG RANGE Lateral:
- Left of CL: 0.10 m
- Right of CL: 0.10 m

Longitudinal:

MAXIMUM WEIGHT 2427 kg (5351 lb)

MINIMUM CREW 1 pilot in left seat

NUMBER OF SEATS 7 maximum (pilot included); or

8, if modification OP 3673 is installed. This optional is to be used in
accordance with the corresponding Flight Manual Supplement.

FUEL CAPACITY Total: 540 liters

Usable fuel: 538.7 liters

OIL CAPACITY Engine: 6.2 liters

MAXIMUM OPERATING 7010 m (23000 ft)

ALTITUDE Refer to Flight Manual for Takeoff and landing

S/N’s ELIGIBLE 3358 and subsequent.

Imported aircraft:
A Certificate of Airworthiness for Export endorsed as noted under "Import
Requirements" must be submitted for each individual aircraft for which
application for a Brazilian Certificate of Airworthiness is made.
Aircraft manufactured in Brazil: see Note 7.
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 14/20

VI - Model EC 130T2 (Normal Category), approved 17 June 2013.

ENGINES Turbomeca Arriel 2D (See TCDS nº EM-9802).

FUEL Jet A, Jet A1, JP1, JP5, JP8, F34, F35, F43 or F44. (See RFM for
emergency fuels)

INSTALLED ENGINE LIMITS Minimum Generator

Limit Torque Temperature
Power Rating Guaranteed Speed***
on Shaft (T4)
Power* Ng (NG)**
INSTALLED ENGINE LIMITS
Max.
(cont.) +1 (102.8%)
transient (5 --- --- ---
( 53569 rpm)
sec.)
Max. at take- 597.5 kw 0 (101.7 %)
951 N.m 949ºC
off (5 min)**** ( 801 hp) ( 52996 rpm)
Max. at take-
597.5 kw 0 (101.7 %)
off(30min) 951 N.m 949ºC
(801 hp) (52996 rpm)
(HIP) ****
Max. 485.7 kw -4 (99.7 %)
773 N.m 905ºC
continuous (651 hp) ( 51954 rpm)
* ISA, ground level at rotor speed 386 rpm
** 100%: 52110 rpm
*** As the actual Ng limitations depend on ambient conditions, the
operational limitations are the Ng values. Ng values correspond to the
maximum Ng reached in the whole flight domain.
**** Use of <takeoff(30min)> power is limited to 30 min. continuous use.
Cumulated use per flight of <takeoff(5 min)> and <takeoff(30min)> powers
is limited to 60 min

ROTOR SPEED LIMITS Power on: 375 to 405 rpm

Power off: Maximum 430 rpm (audio warning ≥ 410 rpm)
Minimum 320 rpm (audio warning = 360 rpm)

TRANSMISSION TORQUE Max. transient (5 s) 104 %

LIMITS Max. take-off: 100 %
Max. continuous: 81.3 %
100% torque = 598 kW at 386 rpm main rotor speed

OIL Refer to Flight Manual for approved engine and gearbox oils.

AIRSPEED LIMITS (IAS) Power-on Never Exceed Speed (VNE)

Absolute VNE: 287 km/h (155 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
In reduced VNE 252 km/h (136 kt) for HP=0 less 18km/h per 2000m
area: (3kt/2000ft) below HP=12750 ft (Refer to Fight
Manual)
Power-off Never Exceed Speed (VNE)
Absolute VNE: 231 km/h (125 kt) for HP=0
In altitude: Speed decreases by 18 km/h per 1000 m (3 kt per
1000 ft)
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 15/20

CG RANGE Lateral:

Longitudinal:

2500 kg (5512 lb)

MAXIMUM WEIGHT

MINIMUM CREW 1 pilot in left seat

NUMBER OF SEATS 7 maximum (pilot included); or

8, if modification OP 3673 is installed. This optional is to be used in
accordance with the corresponding Flight Manual Supplement.

FUEL CAPACITY Total: 540 liters

Usable fuel: 538 liters

OIL CAPACITY Engine: 6.2 liters

MAXIMUM OPERATING 7010 m (23000 ft)

ALTITUDE Refer to Flight Manual for Takeoff and landing
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 16/20

S/N’s ELIGIBLE 7355 and subsequent.

Imported aircraft:
A Certificate of Airworthiness for Export endorsed as noted under "Import
Requirements" must be submitted for each individual aircraft for which
application for a Brazilian Certificate of Airworthiness is made.
Aircraft manufactured in Brazil: see Note 7.

DATA PERTINENT TO ALL MODELS:

DATUM Longitudinal: 3 400 mm ahead of the main rotor head center line.
Lateral: Rotorcraft symmetry plane.

LEVELING MEANS Transmission deck (all AS 350 models).

Mechanical floor (EC 130B4 and EC130T2 models).

MAXIMUM BAGGAGE Baggage compartments loads limitations for all AS350 models:
- R. H. lateral compartment: 100 kg
- L. H. lateral compartment: 120 kg
- Rear compartment: 80 kg
- Rear cabin floor: 310 kg
- Forward cabin floor: 150 kg
Baggage compartments and cargo loads limitations for EC130B4 and
EC130T2 models:
- RH compartment 130 kg 300 kg/m2
- LH compartment 155 kg 300 kg/m2
- Rear compartment 80 kg 145 kg/m2
- Rear cabin floor 495 kg 300 kg/m2
- Forward cabin floor 405 kg 300 kg/m2

ROTOR BLADE AND For rigging information refer to the Maintenance Manual.
CONTROL MOVEMENTS

IMPORT ELIGIBILITY Complete aircraft (all models):

A Brazilian Certificate of Airworthiness may be issued on the basis of on a
EASA Export Certificate on Airworthiness (or a third country Export
Certificate on Airworthiness, in case of used aircraft imported from such
country), including the following statement:
“The aircraft covered by this certificate has been inspected, tested and
found to be in conformity with the Brazilian approved type design as
defined by the Brazilian Type Certificate nº 8812 and in the condition of
safe operation.”

Aircraft kits (AS 350 B2, AS 350 BA and AS 350 B3):

Aircraft kits scheduled for shipment to Brazil for assembly at Helibras will
be accompanied with a conformity certification document JAA Form One
released in accordance with Eurocopter (now AIRBUS HELICOPTERS)
procedures under EASA Production Organization Approval N°F.G.003
(See Production Certification and Notes 4 and 7).

CERTIFICATION BASIS TC Nº 8812 issued in the basis of the following requirements:

a. For the AS350B1, AS350B2, AS350BA and AS350B3 models:
• RBAC (Regulamento Brasileiro da Aviação Cívil) 27, corresponding
to 14 CFR Part 27 - including Amendments 1 through 10 (Normal
Category), effective on 02 May 1976.
• For aircraft equipped with Emergency Floatation System (EFS)
(removable parts P/N / MPN: [223244-0 / 704A42690057]) – as
above with the following additional requirement of CS 27, Amdt. 10,
dated 27 January 2023: 27.1587-b3.
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 17/20

CERTIFICATION BASIS • Special conditions specified in DGAC letters 6518 – SFACT/TC and
(cont.) 6437 – SFACT/TC, dated 17 August 1976 and 28 July 1977,
respectively, related to:
1. Flight conditions
 Take off power check procedure
 Main rotor speed warning
2. Propulsion conditions
 Powerplant control
 Turbine engine bleed air system
3. System and equipment conditions
 Operation without normal electrical power
 Nickel Cadmium battery installation
4. Airframe conditions
 Lightning protection of structure
• Special conditions specified in DGAC letters 971726 -
SFACT/N.HE, dated 03 April 1997 (AS 350B3 version only), related
to:
1. General conditions
 New technology – digital engine control or governor – in-
service endurance demonstration
2. Equipment conditions
 Protection against the effects of HIRF
 Lightning

• For AS350B3 model aircraft incorporating mod. OP-4605

(installation of a fuel system improving crashworthiness) - as above
with requirement §561(c) of FAR 27 at Amdt 32 of 11 June 1986 for
the following elements of the fuel tank lower structure, affected by
this modification: cradles, longitudinal beams, X-stops and rods
(refer to CRI C-03).
• Special Conditions:
- Rechargeable Lithium battery installations (EASA CRI F-24);
- Lightweight Data Recorder installation (EASA CRI F-25).
The noise levels are determined under the conditions prescribed in
chapter 8 and appendix 4 of ICAO Annex 16, Volume 1.
b. For the EC130B4 model:
• RBAC (Regulamento Brasileiro da Aviação Civil) 27, corresponding
to 14 CFR Part 27 - including Amendments 1 through 32 (Normal
Category), effective on 06/11/1996.
• For aircraft equipped with Emergency Floatation System (EFS)
(removable parts P/N / MPN: [223244-0 / 704A42690057]) – as
above with the following additional requirement of CS 27, Amdt. 10,
dated 27 January 2023: 27.1587-b3.
• Special conditions:
1. High Intensity Radiated Field.
• Exemptions:
1. The rear seat bench regarding 27.562 and 27.785 (a), (b) and
(j);
2. Fuel systems regarding 27.952 (a), (c), (d), (f) and (g).
• Equivalent safety finds:
1. Main gearbox oil filter bypass;
2. Powerplant instrument markings.
The noise levels are determined under the conditions prescribed in
chapter 8 and appendix 4 of ICAO Annex 16, Volume 1.
c. For the EC130T2 model (as defined in CRI A-01(X2) issue 6, dated 23
May 2012):
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 18/20

CERTIFICATION BASIS • RBAC (Regulamento Brasileiro da Aviação Civil) 27, corresponding

(cont.) to 14 CFR Part 27 - including Amendments 1 through 32 (Normal
Category), effective on 06/11/1996.
For aircraft incorporating MOD. 074581 (new tail boom: structure
and flight controls) as above with the following amendments as
replacement of the same numbered paragraphs, and the additional
requirements indicated:
− for the rear engine compartment: Sec. 27.351 at Amdt. 27-
34(rear engine cowling), Sec. 27.610 at Amdt. 27-37,
plus EASA CS 27 Appendix A27 at Amdt. 3 (as mentioned in Sec.
27.1529);
− for the tailboom: Sec. 27.610 Amdt. 27-37, Sec. 27.351 Amdt. 27-
34 for the specific rear transmission fairing including thermal
shield area, plus EASA CS 27 Sec. 27.573 Amdt. 3 (composite
spacer, Fenestron one-shot structure), plus EASA CS Appendix
A27 Amdt. 3 (as mentioned in Sec.27.1529);

− for the fenestron structure: Sec. 27.610 Amdt. 27-37, plus EASA
CS 27 Sec. 27.573 Amdt. 3 (composite spacer, Fenestron one-
shot structure), plus EASA CS 27 Appendix A27 Amdt. 3 (as
mentioned in Sec. 27.1529).
The compliance was verified through equivalency finding to EASA
Certification Specification for Small Rotorcraft CS-27 at Amdt 3.
• For aircraft equipped with Emergency Floatation System (EFS)
(removable parts P/N / MPN: [223244-0 / 704A42690057]) – as
above with the following additional requirement of CS 27, Amdt. 10,
dated 27 January 2023: 27.1587-b3.
• Special conditions:
1. High Intensity Radiated Field (CRI F-01(X2));
2. Rotor drive system endurance test for HIP rating (CRI E-
02(X2)).
3. Rechargeable Lithium battery installations (EASA CRI F-24)
4. Lightweight Data Recorder installation (EASA CRI F-25)

• Exemptions:
None
• Equivalent safety finds:
1. Main gearbox oil filter bypass (EC130B4 CRI E4, CRI A-01(X2));
2. Powerplant instrument markings (CRI G-01(X2)).
Noise: RBAC 36 Amendment 28 (eq. ICAO Annex 16, Volume I, 5
Edition, Amendment 9 Chapter1 11 (11.4.1))

REQUIRED EQUIPMENT The basic required equipment, as prescribed in the applicable airworthiness
regulations (see Certification Basis) must be installed in the airplane.

NOTES:

NOTE 1 Weight and balance. Current weight and balance report including the list of equipment
included in the certificated empty weight and loading instructions when necessary, must be
provided for each aircraft at its delivery. The certificated empty weight and corresponding
center of gravity location must include unusable fuel and undrainable oil. To obtain the
proper weight and C. G. information, the helicopter must be jacked up rather than supported
on the skids. If modifications affecting the weight and C. G. are applied to the helicopter,
consult the instructions on the RFM.
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 19/20

NOTE 2 Markings and placards. All markings and placards for passenger information, external
markings for emergency, and load limits in cargo/baggage compartments must be
presented in Portuguese or bilingual (Portuguese and English). The following placard must
be displayed in the clear view of the pilot:
“THE MARKINGS AND PLACARDS INSTALLED ON THIS HELICOPTER
CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH
WHEN OPERATING THIS ROTORCRAFT. OTHER OPERATING LIMITATIONS
WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS ROTORCRAFT
ARE CONTAINED IN THE ROTORCRAFT FLIGHT MANUAL. THE
AIRWORTHINESS LIMITATIONS SECTION OF THE ROTORCRAFT
MAINTENANCE MANUAL MUST BE COMPLIED WITH.”
For the approved markings and placards translations contact the TC holder or STC holder
(as applicable) and/or ANAC at the following address: progcert@anac.gov.br.

NOTE 3 Continuing Airworthiness. Service information, service bulletins, repair manuals, vendor
manuals, rotorcraft flight manuals and maintenance manuals, which contain a statement
that the document is EASA approved, are accepted by the ANAC and are considered ANAC
approved. These approvals pertain to the type design only.
Any alteration to the type design of the rotorcraft may require instructions for Continued
Airworthiness. These instructions must be submitted and accepted by the EASA/ANAC prior
to approval for return to service.
The retirement times of certain parts and inspection requirements listed in the section 5.99
“Airworthiness Limitations” are mandatory. These values of retirement times and
inspections cannot be changed without EASA and ANAC engineering approval.

NOTE 4 The differences of the Brazilian helicopters relating to the basic EASA type design are:
1. The Brazilian Helicopters Flight Manual approved by EASA on behalf of ANAC; and
2. Marking and Placards in Portuguese language or bilingual (see Note 2).

NOTE 5 The weight breakdown and C.G. limit document containing the list of equipment included in
the certificated empty weight and the loading instructions shall accompany the helicopter at
the time of the initial certification and on a permanent basis from that period on. In order to
obtain the most correct weight and C.G. data, the helicopter shall be jacked up its lifting
points rather than using the skids. Should modifications affecting weight and C.G. position
to be incorporated, the Flight Manual instructions shall be referred to.

NOTE 6 The speeds vary constantly as a function of the external conditions (temperature and
altitude) but correspond to a fixed Ng marked “0” on the indicator, which is the limit to be
observed by the pilot on takeoff. For other conditions, the figures in brackets correspond to
Ng values on the instrument.

NOTE 7 Helibras (Brazil) has signed with Eurocopter France (now AIRBUS HELICOPTERS) 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 (now AIRBUS
HELICOPTERS), in conformity to the EASA approved Type design. Helibras helicopters
are produced under Helibras Production Certificate, assembled and tested in accordance
with procedures approved under the French type design by Eurocopter (now AIRBUS
HELICOPTERS) and accepted by the ANAC under the terms and conditions of Helibras
Production Certificate.
Helicopter serial numbers produced by Helibras as the manufacturer are identified in
Eurocopter (now AIRBUS HELICOPTERS) document N° L102-001 – latest revision (list of
serial numbers of stage 2 helicopters produced by Helibras) referenced in both the French
and the Brazilian Type Certificate Data Sheets. The helicopter serial number with prefix
"AS" are equivalent to those ones described in the Eurocopter (now AIRBUS
HELICOPTERS) document N° L102-001, without the prefix "AS" (Serial Number AS 2860
= 2860).
AIRBUS HELICOPTERS 05 September 2024 ER-8812-23 Sheet 20/20

NOTE 8 AS350B3e is a commercial designation of the AS350B3 model which type design
incorporates the following modifications:
• OP-4305 (Arriel 2D engine installation), and additionally
• 07-5601 (Tail rotor control mechanism modification)
• 07-5600 (Tail rotor blade reinforcement)
• 07-8551 (Tail Gear Box control lever modification)

NOTE 9 The TC Holder before 01 January 1992 was:

SOCIÉTÉ NATIONALE INDUSTRIELLE AEROSPATIALE
37, Boulevard de Montmorency
75781 Paris Cedex 16
FRANCE

The TC Holder before 07 January 2014 was:

EUROCOPTER
Aeroport International Marseille-Provence
13725 Marignane
FRANCE

LOG OF REVISIONS
Revision 22 Page 18: Update of Certification Basis and change the
ANAC email address in NOTE 2.

Revision 23 Pages: 16, 17 and 18: Update of Certification Basis and

replace RBHA by RBAC.

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This TCDS is available at ANAC website:
https://sistemas.anac.gov.br/certificacao/Produtos/EspecificacaoOrgE.asp

SEI: 10488505