TCDS NUMBER E34NE

REVISION: 11
DATE: July 16, 2018
U.S. DEPARTMENT OF TRANSPORTATION
SAFRAN HELICOPTER ENGINES
FEDERAL AVIATION ADMINISTRATION
MODELS:
TYPE CERTIFICATE DATA SHEET E34NE
ARRIUS 1A ARRIUS 2F
ARRIUS 2B1 ARRIUS 2K1
ARRIUS 2B1A ARRIUS 2B2
ARRIUS 1A1 ARRIUS 2R

Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E34NE) and other approved data on file
with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and
applicable portions of the Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the approved
manufacturer's manuals and other approved instructions.

TYPE CERTIFICATE (TC) HOLDER Safran Helicopter Engines, S.A.

(formerly Turbomeca S.A.)
64 511 Bordes
France

I. MODELS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS

1A 2B1 2B1A 2F 2K1 2B2 1A1
TYPE Twin spool (free turbine engine); turboshaft engine for helicopters; single stage centrifugal compressor; annular
reverse flow combustion chamber; single gas generator turbine; single stage power turbine (free turbine); reduction
gearbox.
w/o w/
TU45* TU45*
RATINGS (See NOTE 8)

30 sec OEI --- --- --- --- --- --- 747(557) ---
2 min OEI --- --- --- --- --- --- 730(544) ---
2 1/2 minute OEI shp (kw) 520(388) 577(430) 658(491) 705(526) --- 676(504) --- 556(415)
Continuous OEI 479(357) 577(430) 613(457) 498(371) --- 676(504) 650(485) 518(386)
30 minute OEI shp (kw) 479(357) --- --- --- --- --- --- 518(386)
Takeoff shp (kw) 456(340) 577(430) 613(457) 498(371) 432(322) 676(504) 644(480) 460(343)
Max continuous shp (kw) 397(296) 547(408) 547(408) 414(309) 432(322) 579(432) 579(432) 409(305)
* See Note 23

FUEL (See NOTE 15)

FUEL CONTROL Turbomeca full authority digital electronic control system with manual backup mode for the Arrius
1A, Arrius 1A1, Arrius 2B1 and Arrius 2B1A and Arrius 2K1. For the Arrius 2F the fuel control
system is ensured by a hydromechanical control with manual mode.
OIL (See NOTE 14)

PRINCIPAL DIMENSIONS
Length, in (mm) 63(1601) 45.6(1158) -- -- 55.9(1418) 38.3(973) 45.6(1158) 63(1601)
Width, in (mm) 17.2(436) 20.4(518) -- -- 19.3(488) 21.2(538) 20.4(518) 17.2(436)
Height, in (mm) 23.4(586) 27.2(690) -- -- 26.6(674) 25.1(638) 27.2(690) 23.4(586)

*
PAGE 1 2 3 4 5 6 7 8 9 10 11
REV. 11 8 8 8 11 11 8 8 11 10 8
LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL"
“---” INDICATES “DOES NOT APPLY”
NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES, IF ANY
ARE BLACK-LINED IN THE LEFT MARGIN.
TCDS E34NE PAGE 2 of 11

I. MODELS ARRIUS
2R
TYPE The ARRIUS 2R has an annular air intake, a single centrifugal compressor driven by a single stage gas generator
turbine, an annular reverse flow combustion chamber, and a single stage free turbine with a through shaft driving a
reduction gearbox located in the front. The reduction gear unit also includes the accessory gearbox driven by the gas
generator.
With Without
torque and torque and
fuel flow fuel flow
limitations limitations
RATINGS (See NOTE 8)

30 sec OEI rating

2 min OEI rating
2 1/2 minute rating shp (kw)
Continuous OEI rating
30 minute rating shp (kw)
Takeoff shp (kw) 472(352) 505(377)
Max continuous shp (kw) 433(323) 460(343)

FUEL (See NOTE 15)

FUEL CONTROL The Arrius 2R has a dual-channel electronic engine control system with auxiliary fuel metering back-
up control.
OIL (See NOTE 14)

PRINCIPAL DIMENSIONS
Length, in (mm) 36.8(934)
Width, in (mm) 21.8(553)
Height, in (mm) 26.6(676)
TCDS E34NE PAGE 3 of 11

CENTER OF GRAVITY Refer to Installation Manual.

WEIGHT (dry) ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS
1A 2B1 2B1A 2F 2K1 2B2 1A1
pounds (kg), maximum
223.3 246.9 246.9 229.3 248.7 246.9 223.3
(101.3) (112) (112) (104) (112.8) (112) (101.3)

Refer to Installation Manual, for definition of engine dry weight.

DRIVE SHAFT TYPE Refer to Installation Manual.

CENTER OF GRAVITY Refer to Installation Manual.

WEIGHT (dry) ARRIUS
2R
pounds (kg), maximum
264.3
(119.9)

Refer to Installation Manual, for definition of engine dry weight.

DRIVE SHAFT TYPE Refer to Installation Manual.

IGNITION Low tension, high energy system including:

- Twin output (one high energy generator)
- 2 injectors
- 2 ignitors

CERTIFICATION BASIS 14 CFR 21.29 and 14 CFR part 33 effective February 1, 1965, and Amendments 33-1through
Amendment 33-12 for the ARRIUS 1A and 1A1. The ARRIUS 2B1, 2B1A and 2F, 2K1, 2B2
comply with Amendments 33-1 through 33-14, and Amendment 33-15 § 33.28 and Amendment
33-18 § 33.88 for ARRIUS 2B1A. 2K1, 2B2.

The ARRIUS 2R complies with 14 CFR 21.29 and 14 CFR part 33, effective February 1, 1965,
Amendments 33-1 through 33-33 except: 14 CFR 33.14, Amendment 33-14 for the centrifugal
compressor impeller, the power turbine disk, and the power turbine shaft; 14 CFR §§ 33.63 and
33.83, Amendment 33-14 for the whole engine; 14 CFR 33.27, Amendment 33-14 for the whole
engine. Turbomeca elected to comply, for the ARRIUS 2R, with 14 CFR part 34, Amendment 5a,
effective October 23, 2013, for fuel venting only (14 CFR 34.11).

Type Certificate Number E34NE, issued November 8, 1990.

Model Effective Date of Date Model

Number TC Application Added to TC

ARRIUS 1A December 21, 1989 November 8, 1990

ARRIUS 2F November 25, 1996 September 26, 1997
ARRIUS 2B1 April 14, 1997 November 24, 1997
ARRIUS 2K1 June 20, 1997 July 20, 2001
ARRIUS 2B1A April 6, 1999 July 20, 2001
ARRIUS 2B2 February 16, 2001 November 22, 2002
ARRIUS 1A1 June 17, 2007 December 19, 2007
ARRIUS 2R November 4, 2015 November 30, 2016

The ARRIUS 2B has been deleted from the Type Certificate as of July 20, 2001. All Arrius 2B
engines were retrofitted to ARRIUS engine model 2B1

Direction Generale de l’Aviation Civile (DGAC) originally type certificated this engine under its type
certificate Number M20 The FAA validated this product under U.S. Type Certificate Number E34NE.
Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this
product on behalf of France.
TCDS E34NE PAGE 4 of 11

IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be
exported to the United States with the DGAC or EASA airworthiness approval shall have
a EASA Form 1, Authorized Release Certificate. The EASA Form 1 should state that the
engine conforms to the type design approved under the U.S. Type Certificate E34NE, is in
a condition for safe operation, and has undergone a final operational check.
TCDS E34NE PAGE 5 of 11

NOTES

NOTE 1. Permissible Engine Speeds:

A. Maximum gas generator speed, rpm (Ng)

ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS

1A 2B1 2B1A 2F 2K1 2B2 1A1 2R
2 1/2 minute rating 56,140 56,113 -- 55308 56113 --- 56347 ---
OEI continuous rating --- 54,706 -- --- 54706 --- --- ---
30 minute rating 55,300 --- --- --- --- --- 55452 ---
Takeoff rating 54,685 54,706 -- 54,768 54706 54105 54375 54872
Maximum continuous 53,285 53,406 -- 53,956 53406 53564 53397 54066
Transient overspeed 56,280 56,823 -- 56,065 56823 55187 56498 56065
(5 sec. Limit) (20 sec.) (20 sec.)
30 second OEI rating --- --- --- --- --- 57081 --- ---
2 minute OEI rating --- --- --- --- --- 56413 --- ---
Minimum stabilized 35176 35176 35176 34094 32470 32470 35176 34094
speed
Refer to Installation Manual for variation of these limits with ambient conditions.
Refer to Installation Manual or Maintenance Manual for required action if limits are exceeded.

100% = 54,117 rpm

B. Power Shaft Speeds (Percent)

ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS
1A 2B1 2B1A 2F 2K1 2B2 1A1 2R
Maximum stabilized 104 106 -- 104 106 106 104 105
Maximum transient 108 108 -- 110 112 108* 108 112
(5 sec.) (20 sec.) (20 sec.) (20 sec.) (20 sec.) (5 sec.) (20 sec.)
Minimum stabilized 91 94 -- 92 90 94 91 94
Maximum inadvertent --- --- --- 90 --- --- --- 92
transient overspeed in (20 sec.) (20 sec.)
minimum N2 flight
mode

*For ARRIUS 2B2 with TU 145 software modification installed, maximum transient may include up to 2 seconds between
108% and 110%

During starting, operation within the 70 to 85% range (ARRIUS 1A & ARRIUS 1A1), and 75 to 85% range
(ARRIUS 2B1, ARRIUS 2B1A and ARRIUS 2K1) is limited to 20 seconds.

100% power turbine speed = 45,438 rpm (ARRIUS 1A & ARRIUS 1A1), 44,038 rpm (ARRIUS 2B1, ARRIUS
2B1A, and ARRIUS 2B2), 44,009 rpm (ARRIUS 2K1 and ARRIUS 2F), and 42,014
rpm (ARRIUS 2R).

NOTE 2. Maximum Permissible Temperatures:

A. Exhaust Gas T45(oC)

(measured with 4 doubles thermocouples on gas generator turbine diffuser)
ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS ARRIUS
1A 2B1 2B1A 2F 2K1 2B2 1A1 2R
2 1/2 minute OEI 870 945 -- --- 957 --- 886 ---
rating
2 minute OEI rating --- --- --- --- --- 994 --- ---
30 second OEI rating --- --- --- --- --- 1024 --- ---
OEI continuous rating --- 895 -- --- 905 942 --- ---
30 minute OEI rating 800 --- --- --- --- --- 812 ---
Takeoff rating 800 895 -- 870 905 897 773 865
Max. continuous rating 765 855 -- 830 866 879 749 829
Starting (unlimited) 765 810 -- 800 810 819 765 800
Starting (limited to 870 895 -- 870 895 910 870 870
≤ 5 sec.) (10 sec) (10 sec.)
TCDS E34NE PAGE 6 of 11

NOTE 2. Refer to Installation Manual or Maintenance Manual for required action if limits are exceeded.
(Cont'd) See Note 26 for maximum overtemperature limits.

B. Oil (oC) (measured at location defined in the Installation Manual):

Maximum operating: 80 to 110 depending on altitude and type of fuel (ARRIUS 1A & ARRIUS 1A1),
110 (ARRIUS 2F, ARRIUS 2B1, ARRIUS 2B1A, ARRIUS 2K1, ARRIUS 2B2)
110 (ARRIUS 2R)
Minimum for starting: For all models except ARRIUS 2F and ARRIUS 2R: between -50 and -30;
Refer to Installation Manual.
For ARRIUS 2F:
For 5 mm2/s and 3.9 mm2/s oil: -30
For 3 mm2/s oil: -50
For ARRIUS 2R:
For 5 mm2/s and 4 mm2/s oil: -30
For 3 mm2/s oil: -50

Minimum for power application: For all models except ARRIUS 2F and ARRIUS 2R: between 0 and 10,
according to oil specifications. See Installation Manual for further details.
For ARRIUS 2F:
For 5 mm2/s and 3.9 mm2/s oil: 10 (transient condition) and 50 (continuous
operation).
For 3 mm2/s oil: 0 (transient condition) and 50 (continuous operation).
For ARRIUS 2R:
For 5 mm2/s and 4 mm2/s oil: 10 (transient condition) and 50 (continuous
operation).
For 3 mm2/s oil: 0 (transient condition) and 50 (continuous operation).
Fuel (oC) (at engine inlet):

Maximum operating +50 (see NOTE 20) for ARRIUS 1A, and ARRIUS 1A1. For ARRIUS 2F,
ARRIUS 2B1, ARRIUS 2B1A, ARRIUS 2B2, ARRIUS 2K1, and ARRIUS 2R, refer to the Installation Manual.
Minimum for starting: The fuel temperature conditions for engine starting are specified in the Installation Manual.
Use anti-icing additive when fuel temperature is below -15 for ARRIUS 2F and below -20 for ARRIUS 2R. All other
models, refer to Installation/Operating Manual.
Refer to Installation Manual for the definition of normal and restricted fuels for the ARRIUS 2F and ARRIUS 2R.

NOTE 3. Power Turbine Unit Torque Limits ft. lb. (Nm):

ARRIUS ARRIUS ARRIUS 2B1A ARRIUS ARRIUS ARRIUS ARRIUS
1A 2B1 w/o w/ TU45* 2F 2K1 2B2 1A1
TU45*

- Max.,2 1/2 min OEI 501.5 (680) 582.7 (790) 586 (795) 628(852) --- 612.2 (830) --- 501.5 (680)
- Max. OEI
continuous --- 545.8 (740) -- 443(600) --- 560.6 (760) 546(740) ---
- Max. 30 min. OEI 464.7 (630) --- --- --- --- --- --- 464.7 (630)
- Max.,takeoff 464.7 (630) 545.8 (740) -- 443(600) 479.5 (650) 560.6 (760) 546(740) 464.7 (630)
- Max., continuous 413.0 (560) 486.8 (660) -- 369(500) 442.6 (600) 501.5 (680) 486.8(660) 413.0 (560)
- Transient (20 sec.) 568 (770) 612.2 (830) -- 668(905) 554.7 (752) 708.8 (961) --- 568 (770)
- 30 sec OEI --- --- --- --- --- --- 667.4(905) ---
- 2 minute OEI --- --- --- --- --- --- 667.4(905) ---

ARRIUS
2R

- Max.,2 1/2 min OEI ---

- Max. OEI
continuous ---
- Max. 30 min. OEI ---
- Max.,takeoff 442.5(600)
- Max., continuous 405.7(550)
- Transient 486.8(660)
(5 sec.)
* See NOTE 23
TCDS E34NE PAGE 7 of 11

NOTE 4. Fuel and Oil Pressure Limits, psig (bar):

A. Fuel: For all models except ARRIUS 2R: refer to Installation Manual. For ARRIUS 2R: within starting
or relight phase and above 2000m altitude, a prime pump is necessary. This shall maintain a relative
pressure equal to or greater than 25 kPA. The maximum fuel system inlet pressure is 110 kPA relative to
atmospheric pressure.
B. Oil: (measured at engine pump outlet after filter)
ARRIUS 1A ARRIUS 2B1/2B1A ARRIUS 2K1 ARRIUS 2B2 ARRIUS 1A1
Maximum: 145.1 (10) 145.1 (10) 217.7 (15) 145.1 (10) 145.1 (10)

ARRIUS 2F ARRIUS 2R
Maximum differential: 217.6 (15) 217.6 (15)

(refer to Installation Manual or Maintenance Manual if limit is exceeded).

ARRIUS 1A ARRIUS 2B1/2B1A ARRIUS 2K1 ARRIUS 2B2 ARRIUS 1A1
Minimum at N1 greater than percent stated below:
65%: 24.7(1.7) 68%: 24.7(1.7) 60%: 18.85(130) 65%: 24.7(1.7) 65%: 24.7(1.7)

ARRIUS 2F ARRIUS 2R
Minimum differential: 24.7(1.7) *
* See Installation Manual.

NOTE 5. Maximum Permissible Air Bleed:

(P3 air bleed from centrifugal compressor plenum)

- Maximum air mass flow: 0.15 lb/sec. (ARRIUS 1A/1A1), at take-off rating under standard sea level
conditions (Refer to Installation Manual).
4.5% of engine inlet air mass flow (ARRIUS 2B1/2B1A)
5.48% of engine inlet air mass flow (ARRIUS 2K1/2B2).
ARRIUS 2F: Maximum air flow on one port and maximum total bleed air flow is 0.15 lb/sec.
ARRIUS 2R: One port maximum air flow is 0.15 lb/sec. Maximum total bleed air flow is 0.18 lb/sec on the
two ports.
- Power loss due to air bleed: refer to Installation Manual or Performance Booklet.

NOTE 6. Air Intake Requirements:

-The Arrius engines were not tested to evaluate the effects of foreign object ingestion. It is the Airframer's
responsibility to protect the engine from foreign object ingestion through the design of the aircraft air intake.
The aircraft manufacturer must substantiate that the aircraft air intake installation prevents foreign object
ingestion by the engine, prior to the approval of the engine installation.

-The Arrius engines do not have anti-icing provisions. The Arrius 1A & Arrius 1A1 engines comply with the
engine airworthiness requirements during icing conditions when Aerospatiale 335 N helicopter air intake
Part Number (P/N) 335 A543533 is installed. The ARRIUS 2B1, 2B2, 2B1A, 2F and 2K1 engines comply
with the engine airworthiness requirements during icing conditions without the aircraft air intake installed.
Therefore, for the ARRIUS 2B1, 2B1A, 2F and 2K1 engines, prior to the approval of the engine installation,
the aircraft manufacturer shall substantiate that the installation of the air intake does not impact engine
operation during icing conditions. The ARRIUS 2R is approved to be fitted to rotorcraft when the
installation precludes ingestion of hailstone and birds from entering the engine inlet.
TCDS E34NE PAGE 8 of 11

NOTE 7. Accessory Drive Provisions:

ARRIUS 1A and 1A1

Starter-generator output
Rotation Rotation speed Maximum Maximum torque Maximum static
direction (RPM) Continuous at overload overhang moment
Mechnical Power, lb*ft(N*m) lb*ft(N*m)
hp(kW)
CW 11479 (*) 18.4(25) 18.4(25)
Values correspond to 100% Ng. The rotation direction of the engine rotating components is indicated with respect to viewing the engine from the front to
the rear. For further details, see Installation Manual.
* Maximum steady state mechanical off-take:
Arrius 1A: 4.8 kW at all ratings
Arrius 1A1:
Maximum continuous and take-off ratings: 3 kW without de-rating. If mechanical off-take is between 3 and 6 kW, corrections to performance and
ratings stated in Performance Booklet X 319 U1 100 2 shall be applied, and it shall be limited to 4.8 kW if altitude is higher than 10,000 ft.
Continuous OEI rating: 4.8 kW without de-rating. If mechanical off-take is between 4.8 and 6 kW, corrections to performance and ratings stated in
Performance Booklet X 319 U1 100 2 shall be applied, and it shall be limited to 4.8 kW if altitude is higher than 10,000 ft.
2 ½ minute OEI rating: 6 kW without de-rating, and limited to 4.8 kW if altitude is higher than 10,000 ft.

ARRIUS 2B1, 2B1A, 2B2, and 2K1

Starter-generator output
Model Rotation Rotation speed Maximum torque Maximum static Fuse shaft
direction (RPM) in overload overhang moment breakaway
lb*ft(N*m) lb*ft(N*m) torque,
lb*ft(N*m)
ARRIUS 2B1, CW 12334 18.4(25) 18.4(25) 70.1(95)
2B1A, and 2B2
ARRIUS 2K1 CW 12335 18.4(25) 5.2(7) 70.1(95)
Spare drive
ARRIUS 2K1 CW 4632 11.1(15) 11.1(11) 33.2(45)
Values correspond to 100% Ng. The rotation direction of the engine rotating components is indicated with respect to viewing the engine from the front to
the rear. For further details, see Installation Manual.

ARRIUS 2F and ARRIUS 2R

Starter-generator output
Model Rotation Rotation speed Maximum torque Maximum static Fuse shaft Maximum
direction (RPM) in overload overhang moment breakaway Continuous
lb*ft(N*m) lb*ft(N*m) torque, Mechnical Power,
lb*ft(N*m) hp(kW)
ARRIUS 2F CW 12334 18.4(25) 18.4(25) 56.8(77) 7.6(5.7)
ARRIUS 2R CW 12334 18.4(25) 18.4(25) 70.1(95) 9.2(6.9)
Values correspond to 100% Ng. The rotation direction of the engine rotating components is indicated with respect to viewing the engine from the front to
the rear. For further details, see Installation Manual.
TCDS E34NE PAGE 9 of 11

NOTE 8. Engine Ratings: Based on calibrated test rig with performance under the following conditions:

- Static, sea level standard conditions (59oF, 29.92 in. Hg).

- No airbleed, no accessory power extraction.
- Output shaft drive speed 100% = 6016 rpm (ARRIUS 1A/1A1), 5898 rpm (ARRIUS 2B1/2B1A)
- Output shaft drive speed 106% = 6360 rpm (ARRIUS 2K1), 6252 rpm (ARRIUS 2B2).
- Heating value of fuel = 18,550 BTU/lb.

For the ARRIUS 2F:

The performance values specified correspond to minimum values defined under the following conditions:
- ISA conditions at sea level, on test bed
- Engine equipped with a test bed air flow measurement intake plenum and a test bed exhaust jet pipe
- No air bleed
- No power drawn by any accessories other than those required for engine operation
- Power off-take speed 100% = 6000 RPM constant
- Usual fuel heating value = 18,550 Btu/lb
- Alternative fuel heating value = 18,702 Btu/lb

For the ARRIUS 2R:

The performance values specified correspond to minimum values defined under the following conditions:
- Neither pressure drop nor heating, nor swirl, at engine inlet plane 1 (see Installation/Operating Manual §2.2 for
reference plane definition)
- Atmospheric humidity used for performance calculation: Humidity Mixing Ratio = 0.0069 (65% relative humidity
at sea level and 59 °F)
- Engine equipped with a test bed air flow measurement intake plenum and a test bed exhaust jet pipe.
- No back pressure downstream of the test bed exhaust pipe plane 7
- No air bleed
- No electrical power off-take
- No power drawn by any accessories other than those required for engine operation
- Output shaft rotation speed 100% = 5610 RPM constant
- Fuel heating value = 18,550 Btu/lb
- No fuel flow limit

The indicated ratings are minimum final test performance of production and overhaul engines in accordance with
engine acceptance test specification Number 0.319.00.940.0 (ARRIUS 1A/1A1), 0.319.00.958.0 (ARRIUS
2B1/2B1A), 0319.00959.0 (ARRIUS 2F), 0.319.00.962 (ARRIUS 2K1), 0.319.00.967.0 (ARRIUS 2B2).

NOTE 9. Reserved.

NOTE 10. Oil Systems: Refer to Installation Manual.

NOTE 11. Engine Monitoring Transmitters: Refer to Installation Manual.

NOTE 12. Electrical Equipment: Refer to Installation Manual.

NOTE 13. Engine Fire Detector:

Fire detectors provided on the engine: 4 (ARRIUS 1A/1A1), 2 (ARRIUS 2B1/2B1A/2B2), and 3 (ARRIUS 2F)

NOTE 14. Refer to Installation Manual for approved oil specification.

NOTE 15. Refer to Installation Manual for approved fuel and additive specification.

NOTE 16. Life-limited components are listed in DGAC or EASA-approved Chapter 5 or Airworthiness Limitation Chapter/Section
of the Engine Maintenance Manual.
TCDS E34NE PAGE 10 of 11

NOTE 17. Manuals required by 14 CFR 33.4 and 33.5

ARRIUS 1A ARRIUS 2B1 ARRIUS 2B1A ARRIUS 2F ARRIUS 2K1 ARRIUS 2B2 ARRIUS 1A1
Installation/
Operating
Manual x319 D 0012 x319 L5 0012 x319 L5 0012 x319 L6 0012 x319 N1 0042 x319 n3 0012 x319 D6 0012
Maintenance
Manual x319 D 6300 1 x319 L5 3012 x319 L5 4512 x319 L6 3002 x319 N1 3002 x319 n3 4512 x319 U1 451 2
Overhaul
Manual x319 H6 5002 x319 L5 5002 x319 L5 5002 x319 L6 5002 x319 N1 5002 x319 n3 5002 x319 U1 5002

ARRIUS 2R
Installation/ x319 R5 0032
Operating
Manual
Maintenance x319 R5 4602
Manual
Overhaul x319 R5 5002
Manual

The manuals and ICA listed above have been accepted or approved per 14 CFR 33.4 and 33.5

Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or –
for approvals made before September 28, 2003 – by the DGAC. Any such documents are accepted by the FAA and
are considered FAA approved.
• Service bulletins,
• Structural repair manuals,
• Vendor manuals,
• Aircraft flight manuals, and
• Overhaul and maintenance manuals.
These approvals pertain to the type design only.

NOTE 18. Reserved.

NOTE 19. FADEC box (ARRIUS 1A, 1A1, 2B1, 2B1A, 2K1 and 2B2)

A. Installation conditions
The box shall be installed in the airframe outside the fire zone.
Refer to Installation Manual for other installation conditions.

B. Lightning protection: refer to Installation Manual.

C. Electromagnetic interferences: tests carried out are specified in the Installation

Manual.

D. Software
The software has been developed and tested and the corresponding documentation
developed according to the recommendations of documents RTCA DO
178A/EUROCAE ED-12A to level 1.

NOTE 20. ARRIUS 1A, ARRIUS 1A1: Maximum fuel temperature when operating with restricted use-fuels is +25oC. Maximum
operating duration with restricted use fuels is 25 hours.

NOTE 21. The ARRIUS 1A, ARRIUS 1A1 and ARRIUS 2B1, 2B2, 2B1A and ARRIUS 2K1 engines are restricted to twin-engine
rotorcraft applications.

NOTE 22. The ARRIUS 2B engine model is no longer in service and has been cancelled by the FAA from this data sheet as
requested by the manufacturer.

NOTE 23. TU45 is a major non-significant software modification, which mainly increases the ARRIUS 2B1A 2 1/2 minute OEI
power rating and reduces the other power ratings. When modification TU45 is applied on 2B1A, it is identified as
"ARRIUS 2B1A__1" on the engine identification plate.
TCDS E34NE PAGE 11 of 11

NOTE 24. ARRIUS 2F maximum oil tank volume is 1.29 gallons. ARRIUS 2F minimum oil tank volume is 0.79 gallons. The oil
tank is not part of the engine type design for the ARRIUS 2R. The oil consumption limit for both ARRIUS 2F and
ARRIUS 2R is 0.079 gallons/hour.

NOTE 25. The ARRIUS 2F and ARRIUS 2R have not been approved for time limited dispatch.

NOTE 26. The engine is approved for a maximum exhaust gas overtemperature for inadvertent use due to abnormal operation for
the time periods stated without requiring rejection of the engine from service or maintenance action other than to
correct the cause. The cause of the overtemperature must be investigated and corrected. The maximum overtemperature
limit for the ARRIUS 2F is 900 °C for 5 seconds. The maximum overtemperature limit for the ARRIUS 2R is 882 °C
for 20 seconds.

--END--