# TCDS E34NE: Safran Helicopter Engines S.A. - Type: Type certificate data sheet - Status: Current - Holder: Safran Helicopter Engines S.A. - Revision: 13 - Revised: April 22, 2022 - Product: Engine - Certification basis: Part 21, Part 33, Part 21, Part 33, Part 21, Part 33, Part 21, Part 33, Part 21, Part 33, Part 21, Part 33, Part 21, Part 33, Part 21, Part 33 - Registered aircraft: 345, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/3d/aa/3daa80b16766dd97976cd209a2d63894e792aa10c668c2cf541764c9bcf7e947 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/D98F6F7BAC6F30B386258845006AC22D.0001 - Page: https://openairdocs.org/tcds/E34NE ## Models (8) As the data sheet lists them. - Arrius 1A - Arrius 2B1 - Arrius 2B1A - Arrius 1A1 - Arrius 2K1 - Arrius 2F - Arrius 2B2 - ARRIUS 2R ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text * PAGE 1 2 3 4 5 6 7 8 9 10 11 REV. 13 13 13 13 13 13 13 13 11 13 13 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" “---” INDICATES “DOES NOT APPLY” NOTICE: SEVERAL PAGES HAVE BEEN REFORMATTED. SIGNIFICANT CHANGES, ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E34NE TCDS NUMBER E34NE REVISION: 13 DATE: April 22, 2022 SAFRAN HELICOPTER ENGINES MODELS: 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.) 64 510 Bordes France I. MODELS ARRIUS 1A ARRIUS 2B1 ARRIUS 2B1A ARRIUS 2F TYPE The engine models have 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. without TU45* with TU45* without Tf39(**) with Tf39(**) With torque and fuel flow limitations Without torque and fuel flow limitations With torque and fuel flow limitations Without torque and fuel flow limitations RATINGS (See NOTE 8) 30 sec OEI 2 min OEI 2 1/2 minute OEI shp (kw) Continuous OEI 30 minute OEI shp (kw) Takeoff shp (kw) Max continuous shp (kw) --- --- 520(388) 479(357) 479(357) 456(340) 397(296) --- --- 577(430) 577(430) --- 577(430) 547(408) --- --- 658(491) 613(457) --- 613(457) 547(408) --- --- 705(526) 498(371) --- 498(371) 414(309) --- --- --- --- --- 432(322) 432(322) --- --- --- --- --- 504(376) 449(335) --- --- --- --- --- 504(376) 449(335) --- --- --- --- --- 504(376) 449(335) * See Note 23 ** See Note 27 FUEL (See NOTE 15) FUEL CONTROL OIL (See NOTE 14) Turbomeca full authority digital electronic control system with manual backup mode for the Arrius 1A, Arrius 2B1 and Arrius 2B1A. The Arrius 2F Fuel control system is ensured by a hydromechanical control with manual mode. TCDS E34NE PAGE 2 of 11 PRINCIPAL DIMENSIONS Length, in (mm) Width, in (mm) Height, in (mm) 63(1601) 17.2(436) 23.4(586) 45.6(1158) 20.4(518) 27.2(690) - - - - - - - - - - - - 55.9(1418) 19.3(488) 26.6(674) I. MODELS ARRIUS 2K1 ARRIUS 2B2 ARRIUS 1A1 ARRIUS 2R TYPE The engine models have 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 torque and fuel flow limitations Without torque and fuel flow 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) Max continuous shp (kw) --- --- 676(504) 676(504) --- 676(504) 579(432) 747(557) 730(544) --- 650(485) --- 644(480) 579(432) --- --- 556(415) 518(386) 518(386) 460(343) 409(305) 472(352) 433(323) 522(389) 476(355) FUEL (See NOTE 15) FUEL CONTROL Turbomeca full authority digital electronic control system with manual backup mode for the Arrius 2K1, Arrius 2B2 and Arrius 1A1. 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) Width, in (mm) Height, in (mm) 38.3(973) 21.2(538) 25.1(638) 45.6(1158) 20.4(518) 27.2(690) 63(1601) 17.2(436) 23.4(586) 36.8(934) 21.8(553) 26.6(676) TCDS E34NE PAGE 3 of 11 CENTER OF GRAVITY Refer to Installation Manual. WEIGHT (dry) pounds (kg), maximum ARRIUS 1A 223.3 (101.3) ARRIUS 2B1 246.9 (112) ARRIUS 2B1A 246.9 (112) ARRIUS 2F 229.3 (104) ARRIUS 2K1 248.7 (112.8) ARRIUS 2B2 246.9 (112) 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) pounds (kg), maximum ARRIUS 1A1 223.3 (101.3) ARRIUS 2R 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. 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. NOTES NOTE 1. Permissible Engine Speeds: A. Maximum gas generator speed, rpm (Ng) ARRIUS 1A ARRIUS 2B1 ARRIUS 2B1A ARRIUS 2F ARRIUS 2K1 ARRIUS 2B2 ARRIUS 1A1 ARRIUS 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 (5 sec. Limit) 56,280 56,823 - - 56,065 (20 sec.) 56823 55187 56498 56065 (20 sec.) 30 second OEI rating --- --- --- --- --- 57081 --- --- 2 minute OEI rating --- --- --- --- --- 56413 --- --- Minimum stabilized speed 35176 35176 35176 34094 32470 32470 35176 34094 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 1A ARRIUS 2B1 ARRIUS 2B1A ARRIUS 2F ARRIUS 2K1 ARRIUS 2B2 ARRIUS 1A1 ARRIUS 2R Maximum stabilized 104 106 - - 104 106 --- 104 105 Maximum transient 108 (5 sec.) 108 (20 sec.) - - 110 (20 sec.) 112 (20 sec.) 108 (20 sec.) 108 (5 sec.) 112 (20 sec.) Minimum stabilized 91 94 - - 92 90 94 91 94 Maximum inadvertent transient overspeed in minimum N2 flight mode --- --- --- 90 (20 sec.) --- --- --- 92 (20 sec.) *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) TCDS E34NE PAGE 5 of 11 NOTE 2. Maximum Permissible Temperatures: A. Exhaust Gas T45(oC) (measured with 4 doubles thermocouples on gas generator turbine diffuser) ARRIUS 1A ARRIUS 2B1 ARRIUS 2B1A ARRIUS 2F ARRIUS 2K1 ARRIUS 2B2 ARRIUS 1A1 ARRIUS 2R 2 1/2 minute OEI rating 870 945 - - --- 957 --- 886 --- 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 - - 830 866 897 749 829 Starting (unlimited) 765 810 - - 800 810 819 765 800 Starting (limited to ≤ 5 sec.) 870 895 - - 870 (10 sec) 895 910 870 870 (10 sec.) Refer to Installation Manual or Maintenance Manual for required action if limits are exceeded. 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 oil (ARRIUS 1A & ARRIUS 1A1), 110 (ARRIUS 2F, ARRIUS 2B1, ARRIUS 2B1A, ARRIUS 2K1, ARRIUS 2B2 and ARRIUS 2R) Minimum for starting: For all models except ARRIUS 2F and ARRIUS 2R: between -50 and -30; Refer to Installation Manual for further details. 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. Refer to 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). C. 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. TCDS E34NE PAGE 6 of 11 NOTE 3. Power Turbine Unit Torque Limits ft. lb. (Nm): ARRIUS 1A ARRIUS 2B1 ARRIUS 2B1A ARRIUS 2F ARRIUS 2K1 ARRIUS 2B2 w/o TU45* w/ TU45* - Max.,2 1/2 min OEI - Max. OEI continuous - Max. 30 min. OEI - Max.,takeoff - Max., continuous - Transient (20 sec.) - 30 sec OEI - 2 minute OEI 501.5 (680) --- 464.7 (630) 464.7 (630) 413.0 (560) 568 (770) --- --- 582.7 (790) 545.8 (740) --- 545.8 (740) 486.8 (660) 612.2 (830) --- --- 586 (795) - - --- - - - - - - --- --- 628(852) 443(600) --- 443(600) 369(500) 668(905) --- --- --- --- --- 479.5 (650) 442.6 (600) 554.7 (752) --- --- 612.2 (830) 560.6 (760) --- 560.6 (760) 501.5 (680) 708.8 (961) --- --- --- 546 (740) --- 546 (740) 486.8(660) --- 667.4(905) 667.4(905) ARRIUS 1A1 ARRIES 2R - Max.,2 1/2 min OEI 501.5 (680) --- - Max. OEI continuous --- --- - Max. 30 min. OEI 464.7 (630) --- - Max.,takeoff 464.7 (630) 442.5(600) - Max., continuous 413.0 (560) 405.7(550) - Transient (20 sec.) 568 (770) 486.8(660) (5 sec.) * See NOTE 23 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. TCDS E34NE PAGE 7 of 11 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. NOTE 7. Accessory Drive Provisions: ARRIUS 1A and 1A1 Starter-generator output Rotation direction Rotation speed (RPM) Maximum Continuous Mechnical Power, hp(kW) Maximum torque at overload lb*ft(N*m) Maximum static overhang moment lb*ft(N*m) 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. TCDS E34NE PAGE 8 of 11 NOTE 7 Cont’d Accessory Drive Provisions: ARRIUS 2B1, 2B1A, 2B2, and 2K1 Starter-generator output Model Rotation direction Rotation speed (RPM) Maximum torque in overload lb*ft(N*m) Maximum static overhang moment lb*ft(N*m) Fuse shaft breakaway torque, lb*ft(N*m) ARRIUS 2B1, 2B1A, and 2B2 CW 12334 18.4(25) 18.4(25) 70.1(95) 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 direction Rotation speed (RPM) Maximum torque in overload lb*ft(N*m) Maximum static overhang moment lb*ft(N*m) Fuse shaft breakaway torque, lb*ft(N*m) Maximum Continuous Mechnical Power, 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 Installation/ Operating Manual Maintenance Manual Overhaul Manual X 319 D 001 2 X 319 D 6300 1 X 319 H6 5002 X 319 L5 001 2 X 319 L5 301 2 X 319 L6 501 2 X 319 L5 001 2 X 319 L5 451 2 X 319 L6 501 2 X 319 L6 001 2 X 319 L6 301 2 X 319 L6 501 2 X 319 N1 004 2 X 319 N1 300 2 X 319 L6 501 2 X 319 N3 001 2 X 319 N3 451 2 X 319 L6 501 2 ARRIUS 1A1 ARRIUS 2R Installation/ Operating Manual X 319 D6 001 2 X 319 R5 003 2 Maintenance Manual X 319 U1 451 2 X 319 R5 460 2 Overhaul Manual X 319 U1 500 2 X 319 R5 501 2 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. NOTE 27 Tf39 is a major non-significant modification. The purpose of this modification is to adjust the Fuel Control Unit maximum flow in order to avoid torque limitations when operating with JP4 fuel. A consequence is that the maximum air flow extracted can be increased up to flow rate of 110 g/s (at Take-off power rating under standard ground conditions) when Tf39 is embodied. --END-- ``` ## ADs (37, in force first) - [AD 2026-19-03](https://openairdocs.org/ad/2026-19-03): Engine (Turbine/Turboprop) · Safran Helicopter Engines Arrius 2B2. Effective Nov 2, 2026 - [AD 2026-08-12](https://openairdocs.org/ad/2026-08-12): Engine Fuel Pump · Safran Helicopter Engines Arrius 2F. Effective Jun 2, 2026 - [AD 2025-13-07](https://openairdocs.org/ad/2025-13-07): Engine Fuel and Control · Safran Helicopter Engines Arrius 2B2. Effective Aug 6, 2025 - [AD 2024-24-02](https://openairdocs.org/ad/2024-24-02): Engine Fuel Pump · Safran Helicopter Engines Arrius 2F. Effective Dec 10, 2024 - [AD 2023-24-09](https://openairdocs.org/ad/2023-24-09): Engine Indicating System · Safran Helicopter Engines ARRIUS 2R. Effective Jan 17, 2024 - [AD 2023-15-03](https://openairdocs.org/ad/2023-15-03): Engine (Turbine/Turboprop) · Safran Helicopter Engines Arrius 2B2. Effective Sep 7, 2023 - [AD 2021-26-26](https://openairdocs.org/ad/2021-26-26): Engine Controls · Safran Helicopter Engines Arrius 2B1, Arrius 2B1A and Arrius 2B2. Effective Feb 23, 2022 - [AD 2021-17-05](https://openairdocs.org/ad/2021-17-05): Fuel Controlling System · Safran Helicopter Engines Arrius 2B1, Arrius 2B1A, Arrius 2B2 and 1 more. Effective Oct 12, 2021 - [AD 2018-12-03](https://openairdocs.org/ad/2018-12-03): Fuel Controlling System · Safran Helicopter Engines Arrius 2B1 and Arrius 2F. Effective Aug 9, 2018 - [AD 2018-07-17](https://openairdocs.org/ad/2018-07-17): Turbine Section · Safran Helicopter Engines Arrius 2B1, Arrius 2B1A, Arrius 2B2 and 1 more. Effective Apr 27, 2018 - [AD 2018-05-03](https://openairdocs.org/ad/2018-05-03): Engine Oil System (Airframe Furnished) · Safran Helicopter Engines Arrius 2F. Effective Mar 21, 2018 - [AD 2015-17-18](https://openairdocs.org/ad/2015-17-18): Oil pump · Turbomeca Arrius 2F. Effective Oct 2, 2015 - [AD 2015-10-07](https://openairdocs.org/ad/2015-10-07): Ejector assembly nozzle · Turbomeca Arrius 2F. Effective Jun 12, 2015 - [AD 2012-07-09](https://openairdocs.org/ad/2012-07-09): P3 air pipe (first section) and the RH rear half-wall · Turbomeca Arrius 2F. Effective May 24, 2012 - [AD 2009-21-11](https://openairdocs.org/ad/2009-21-11): Cycle life limit value for ARRIUS 1A balancing piston. · Turbomeca Arrius 1A. Effective Nov 20, 2009 - [AD 2009-14-01](https://openairdocs.org/ad/2009-14-01): Check valve piston · Turbomeca Arrius 2F. Effective Aug 3, 2009 - [AD 2008-19-11](https://openairdocs.org/ad/2008-19-11): Electronic control (EEC) unit · Turbomeca Arrius 2B1, Arrius 2B1A, Arrius 2B2 and 1 more. Effective Oct 8, 2008 - [AD 2008-13-27](https://openairdocs.org/ad/2008-13-27): Propeller · Turbomeca Arrius 2F. Effective Aug 6, 2008 - [AD 2007-11-06](https://openairdocs.org/ad/2007-11-06): Constant delta pressure (delta P) diaphragm · Turbomeca Arrius 2F. Effective Jun 26, 2007 - [AD 2006-26-07](https://openairdocs.org/ad/2006-26-07): A simultaneous interruption of the lubrication on both engines may lead to a double non-commanded in-flight shutdown. · Turbomeca Arrius 2B1, Arrius 2B1A and Arrius 2B2. Effective Jan 18, 2007 - [AD 2005-17-15](https://openairdocs.org/ad/2005-17-15): Fuel filter-holder assembly · Turbomeca Arrius 2F. Effective Sep 12, 2005 - [AD 2005-11-01](https://openairdocs.org/ad/2005-11-01): Free Turbine Overspeed Protection System · Turbomeca Arrius 1A. Effective Jun 13, 2005 - [AD 2005-09-51](https://openairdocs.org/ad/2005-09-51): Module 2 · Turbomeca Arrius 2F. Effective Jun 3, 2005 - [AD 2003-19-06](https://openairdocs.org/ad/2003-19-06): Gas generator high pressure (HP) turbine disk · Turbomeca Arrius 2B1, Arrius 2B1A and Arrius 2K1. Effective Oct 22, 2003 - [AD 2003-11-10](https://openairdocs.org/ad/2003-11-10): Fuel Flow Mechanical Stop Position · Turbomeca Arrius 2F. Effective Jul 3, 2003 - [AD 2002-01-02](https://openairdocs.org/ad/2002-01-02): Main Fuel Injectors · Turbomeca Arrius 1A. Effective Jan 22, 2002 - [AD 2000-06-09](https://openairdocs.org/ad/2000-06-09): Fuel Injection System · Turbomeca Arrius 1A. Effective Jun 12, 2000 - [AD 2014-04-06](https://openairdocs.org/ad/2014-04-06) (historical): Hydro-mechanical metering unit (HMU) · Turbomeca Arrius 2B1, Arrius 2B1A, Arrius 2B2 and 1 more. Effective Mar 31, 2014 - [AD 2014-01-01](https://openairdocs.org/ad/2014-01-01) (historical): Ejector assembly nozzle · Turbomeca Arrius 2F. Effective Feb 6, 2014 - [AD 2013-11-09](https://openairdocs.org/ad/2013-11-09) (historical): Fuel injection manifolds and the privilege injector · Turbomeca Arrius 2B1 and Arrius 2F. Effective Jul 5, 2013 - [AD 2009-14-11](https://openairdocs.org/ad/2009-14-11) (historical): P3 air pipe · Turbomeca Arrius 2F. Effective Aug 19, 2009 - [AD 2005-17-17 R1](https://openairdocs.org/ad/2005-17-17-R1) (historical): O-rings on the check valve piston · Turbomeca Arrius 2F. Effective Mar 21, 2007 - [AD 2001-08-14 R1](https://openairdocs.org/ad/2001-08-14-R1) (historical): Right injector half manifold and left injector half manifold · Turbomeca Arrius 2B, Arrius 2B1 and Arrius 2F. Effective Feb 23, 2006 - [AD 2005-19-10](https://openairdocs.org/ad/2005-19-10) (historical): Fuel control units (FCUs) · Turbomeca Arrius 2F. Effective Oct 3, 2005 - [AD 2005-17-17](https://openairdocs.org/ad/2005-17-17) (historical): Check valve piston in the lubrication unit · Turbomeca Arrius 2F. Effective Sep 12, 2005 - [AD 2005-12-08](https://openairdocs.org/ad/2005-12-08) (historical): Engine Electronic Control Unit (EECU) · Turbomeca Arrius 2B1, Arrius 2B1A and Arrius 2B2. Effective Jun 29, 2005 - [AD 2001-08-14](https://openairdocs.org/ad/2001-08-14) (historical): Fuel Injector Manifold · Turbomeca Arrius 2B, Arrius 2B1 and Arrius 2F. Effective May 31, 2001 ## Registered aircraft by registry model (OpenAirDocs) - [Safran ARRIUS-2R](https://openairdocs.org/engine/safran-arrius-2r): 144 aircraft (registry code 59992) - [Turbomeca ARRIUS-2F](https://openairdocs.org/engine/turbomeca-arrius-2f): 62 aircraft (registry code 60010) - [Turbomeca ARRIUS-2B2](https://openairdocs.org/engine/turbomeca-arrius-2b2): 48 aircraft (registry code 60012) - [Safran ARRIUS-2B2](https://openairdocs.org/engine/safran-arrius-2b2): 38 aircraft (registry code 59991) - [Turbomeca ARRIUS-2B](https://openairdocs.org/engine/turbomeca-arrius-2b-series): 19 aircraft (registry code 60013) - [Turbomeca ARRIUS-2R](https://openairdocs.org/engine/turbomeca-arrius-2r): 14 aircraft (registry code 60085) - [Turbomeca ARRIUS-2B1](https://openairdocs.org/engine/turbomeca-arrius-2b1): 13 aircraft (registry code 60015) - [Turbomeca ARRIUS-1A](https://openairdocs.org/engine/turbomeca-arrius-1a): 5 aircraft (registry code 60011) - [Turbomeca ARRIUS-2B1A](https://openairdocs.org/engine/turbomeca-arrius-2b1a): 1 aircraft (registry code 60068) - [Turbomeca ARRIUS-2K1](https://openairdocs.org/engine/turbomeca-arrius-2k1): 1 aircraft (registry codes 60055, 60069) - [Safran ARRIUS-2B1A](https://openairdocs.org/engine/safran-arrius-2b1a): 0 aircraft (registry code 59993) --- 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.