# TCDS E00061EN: Rolls-Royce Deutschland Ltd & Co KG - Type: Type certificate data sheet - Status: Current - Holder: Rolls-Royce Deutschland Ltd & Co KG - Revision: 4 - Revised: March 23, 2007 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 11, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/32/d9/32d94b2b1c2032c95f921186a124f88fcd921c8dd763c9807b3be43d1d4c4212 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/96DE5F9C8D8DC161862572A60049BC9B.0001 - Page: https://openairdocs.org/tcds/E00061EN ## Models (3) As the data sheet lists them. - BR700-715A1-30 - BR700-715B1-30 - BR700-715C1-30 ## 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 REV. 4 4 3 3 4 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "DOES NOT APPLY" NOTICE: SIGNIFICANT CHANGES, IF ANY ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00061EN TCDS NUMBER E00061EN REVISION: 4* DATE: March 23, 2007 Rolls-Royce Deutschland Ltd & Co KG MODELS: BR700-715A1-30 BR700-715B1-30 BR700-715C1-30 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00061EN) 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 Rolls-Royce Deutschland Ltd & Co KG (formerly known as BMW Rolls-Royce GmbH and BMW Rolls-Royce Aero Engines) Postfach 1536 D-15827 Dahlewitz G e r m a n y I. MODELS BR700-715A1-30 BR700-715B1-30 BR700-715C1-30 TYPE Two spool axial flow engine consis ting of a single stage fan, a two stage booster, a ten stage axial flow compressor, an annular combustion chamber, a two stage axial flow high pressure turbine, a three stage axial flow low pressure turbine, an accessory gearbox, and a Full Authority Digital Engine Control (FADEC). RATINGS (See NOTE 5) Maximum Continuous Thrust lbf/kN (See NOTE 18) Takeoff Thrust, lbf/kN (See NOTE 18) 17,700/78.74 18,710/83.23 20,160/89.68 20,160/89.68 20,420/90.84 21,430/95.33 EQUIPMENT In accordance with the Type Design Definition. Approved equipment is listed in BRR report E-TR494/97(FR), Issue 4 “Engine Equipment Classification”, or later approved issues. OVERALL DIMENSIONS (mm/in) Length Diameter 3738/147.2 1638/64.5 3738/147.2 1638/64.5 3738/147.2 1638/64.5 WEIGHT (DRY) (kg/lbs) 2085/4595.5 2085/4595.5 2085/4595.5 TCDS E00061EN PAGE 2 CERTIFICATION BASIS FAR 33, effective February 1, 1965, as amended by 33-1 through 33-18 inclusive, including draft FAR’s 33.76 and 33.78, and FAR 34. MODEL APPLICATION DATE TYPE CERTIFICATE ISSUED TYPE CERTIFICATE CANCELED BR700-715A1-30 BR700-715B1-30 BR700-715C1-30 Dec. 19, 1995 Dec. 19, 1995 Dec. 19, 1995 Sep. 1, 1998 Sep. 1, 1998 Sep. 1, 1998 The aviation authority for Germany, Luftfahrt-Bundesamt, type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E00061EN. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with Luftfahrt-Bundesamt (Germany) or EASA airworthiness approval shall have a Joint Aviation Authorities (JAA) or EASA Form 1, Authorized Release Certificate. The JAA or EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E00061EN, is in a condition for safe operation and has undergone a final operational check. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products, imported into the United States. NOTES NOTE 1. Maximum Rotational Speeds: Low Pressure Turbine N1 (RPM) -Maximum Take-off (See NOTE 18) -Maximum Continuous -Maximum Overspeed (20 sec.) -Reverse Thrust (max. 30 sec.) -Emergency Reverse Thrust 6096 6096 6204 3810 5576 High Pressure Turbine N2 (RPM) -Maximum Take-off (See NOTE 18) - Maximum Continuous -Maximum Overspeed (20 sec.) 16661 16661 16744 100% N1 equals 6,195 RPM 100% N2 equals 15,898 RPM TCDS E00061EN PAGE 3 NOTE 2. Temperature Limits Turbine Gas Temperature (Trimmed) oC/oF Takeoff (See NOTE 18) Maximum Continuous Maximum Overtemperature (max 20 sec) Maximum prior to start Starting on ground Starting in flight 900/1652 850/1562 915/1679 150/302 700/1292 850/1562 Oil temperatures (oC/oF) Minimum for Starting Minimum for Accel- eration for take-off Maximum -40/-40 20/68 160/320 Fuel Temperatures (oC/oF) LP Pump Inlet, Max. HP Pump Outlet, Max. 54/129 160/320 (185/365)* LP Pump Inlet Min. Take-off, climb, go- around Flight above 15,000 ft. -42/-44 -48/-54 (* Transiently permitted for a period of not more than 15 minutes.) NOTE 3 Fuel and Oil Pressure Limits Fuel Pressure Miniumum at LP fuel pump inlet: 13.79 kPa/2.0 psig + true vapor pressure Differential Oil Pressures: Mi nimum Acceptance for Flight in the Range: Idle to 11514 RPM N2: 11514 RPM N2 to 14293 N2: Above 14293 RPM N2: Minimum to Complete Flight: Idle to 11514 RPM N2: 11514 RPM N2 to 14293 N2: Above 14293 RPM N2: 241.2 kPa/35 psig straight line interpolation from 241.2 kPa/35 psig to 310.3 kPa/45 psig 310.3 kPa/45 psig 172.4 kPa/25 psig straight line interpolation from 172.4 kPa/25 psig to 241.3 kPa/35 psig 241.3 kPa/35 psid TCDS E00061EN PAGE 4 NOTE 4. Bleed Extraction: EPR = P50/P20: The amounts of bleed extraction from stages 5 and 8 respectively are related to the core entry mass flow, W26. The amount of fan bleed extraction is related to the bypass mass flow, W12. Normal flow represents maximum bleed to be used for normal twin engine operation. Maximum flow represents cabin air bleed for single or twin engine operation and maximum anti- ice bleed. Power Range Maximum Flow (%) Stage 5 Stage 8* Fan Idle to 1.15 EPR 9 15 1.4 1.15 to 1.25 EPR 10 10 1.5 1.25 to 1.3 EPR 10 10 1.5 Above 1.3 EPR 10 10 1.5 * Stage 8 bleed is cleared for operation up to and including Maximum Continuous rating. NOTE 5. The ratings are defined at sea level ISA standard day conditions using a defined test bed configuration for the air intake and exhaust systems with all optional bleeds closed and the aircraft service equipment drives unloaded, at a fuel low heat value of 43179 kJ/kg (22721 CHU/kg). NOTE 6. ACCESSORY DRIVE PROVISIONS for ALL MODELS: Direction* of Rotation 1 Transmission Ratio Shear Neck Torque Lbs-in (daNcm) Weight Lbs (kg) Static Overhang Moment (Lbs-in) (daNcm) Maximum Power Extraction (hp) (kW) Hydraulic Pump CCW 0.234 1496-2000 (1690-2260) 19.84 (9.0) 73.4 (82.9) 24.9 (18.6) Integrated Drive Generator CW 0.501 3150-3651 (3559-4125) 71.9 (32.61) 500 (565.0) 96.4 (71.9) *CW: clockwise; CCW: counterclockwise, looking normal to pad along shaft NOTE 7. Operating and Service Instructions for all models: Installation Drawing and Manual E-TR216/98 (FR) Issue 1 Operating Instructions OI-715-3BR Maintenance Manual M-715-3BR Engine Manual E-715-3BR Time Limits Manual T-715-3BR NOTE 8. The engine is approved for operation with the Boeing thrust reverser (not part of the engine): Assembly number, P/N 715-0021-505 for left hand and right hand installations. NOTE 9. The BR700-715 series engines meet Federal Avia tion Administration requirements for adequate turbine disk integrity and rotor blade containment and does not require external armoring. Certain engine parts are life limited. These limits are listed in the BR715 Time Limits Manual. NOTE 10. Full Authority Digital Engine Control (FADEC): Electronic Engine Control (EEC) Part Number (P/N) 111E9430G609 or later approved standards for the BR700-715 series engines. The EEC software has been developed and verified in accordance with RTCA/DO-178B (The software standard is included in the P/N). NOTE 11. Lightning and EMI protection capability of the elect ronic engine control system, are specified in the BR700-715 Installation Manual. TCDS E00061EN PAGE 5 NOTE 12. Engine overhauls are permitted by the manufacturer only, as long as the Engine Manual is not available. NOTE 13. Information on engine operation with FADEC sy stem dispatch limitations is contained in report E- TR436/98 (FR) Issue 01 or later approved issues for all models. NOTE 14. The engine meets the smoke and hydrocar bon emission requirements of FAR 34 and the carbon monoxide and nitrogen oxide requirements of International Civil Aviation Organization Standards NOTE 15. The BR715 engine meets the fuel ve nting emissions requirements of FAR 34. NOTE 16. Approved fuels and fuel additives are listed in th e latest issue of the BR715 Operating Instruction, OI- 715-3BR. NOTE 17. Approved oils are listed in the latest issu e of the BR715 Operating Instructions, OI-715-3BR. NOTE 18. Use of takeoff thrust for more than five minutes (not to exceed ten minutes) is approved for use only in the event of an inoperative engine due to shutdown or failure. NOTE 19. The maximum permissible engine inlet distorti on limit is specified in the applicable BR715 Installation Manual. NOTE 20. 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 Luftfahrt-Bundesamt (Germany) or CAA (UK). Any such documents including those approved under a delegated authority, 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. • Techinical Variances These approvals pertain to the type design only. ---THE END--- ``` ## ADs (13, in force first) - [AD 2026-21-04](https://openairdocs.org/ad/2026-21-04): Engine (Turbine/Turboprop) · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Nov 23, 2026 - [AD 2023-17-11](https://openairdocs.org/ad/2023-17-11): Turbine Engine Compressor Section · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Sep 20, 2023 - [AD 2021-14-03](https://openairdocs.org/ad/2021-14-03): Turbine Section · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Aug 19, 2021 - [AD 2014-08-05](https://openairdocs.org/ad/2014-08-05): Low-pressure compressor (LPC) case ice impact panels · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective May 23, 2014 - [AD 2014-07-02](https://openairdocs.org/ad/2014-07-02): High-pressure (HP) compressor stages 1 to 6 rotor disc assemblies · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective May 8, 2014 - [AD 2012-14-01](https://openairdocs.org/ad/2012-14-01): LP compressor booster rotor · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Oct 19, 2012 - [AD 2009-07-01 R1](https://openairdocs.org/ad/2009-07-01-R1): High-pressure (HP) turbine stage 1 discs, and HP turbine stage 2 discs · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Aug 6, 2012 - [AD 2009-21-04](https://openairdocs.org/ad/2009-21-04): Engine Failure · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Dec 3, 2009 - [AD 2009-04-13](https://openairdocs.org/ad/2009-04-13): Low pressure (LP) compressor (fan) · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Mar 26, 2009 - [AD 2005-16-12](https://openairdocs.org/ad/2005-16-12): Independent Overspeed Protection (IOP) unit. · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Aug 26, 2005 - [AD 2000-25-51](https://openairdocs.org/ad/2000-25-51): High Pressure Turbine Disks · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Feb 20, 2001 - [AD 2012-26-14](https://openairdocs.org/ad/2012-26-14) (historical): High-pressure (HP) compressor stages 1 to 6 rotor disc assembly · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Jan 10, 2013 - [AD 2009-07-01](https://openairdocs.org/ad/2009-07-01) (historical): High Pressure (HP) Turbine · Rolls-Royce Deutschland BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30. Effective Apr 27, 2009 ## Registered aircraft by registry model (OpenAirDocs) - [Rolls-Royce Deutschland BR700-715A130](https://openairdocs.org/engine/rolls-royce-deutschland-br700-715a130): 6 aircraft (registry code 54006) - [BMW Rolls BR700-715A130](https://openairdocs.org/engine/bmw-rolls-br700-715a130): 1 aircraft (registry code 09499) - [BMW Rolls BR700-715C130](https://openairdocs.org/engine/bmw-rolls-br700-715c130): 1 aircraft (registry code 09497) - [Rolls-Royce BR700-715C1-3](https://openairdocs.org/engine/rolls-royce-br700-715c1-3-series): 1 aircraft (registry code 54574) - [Rolls-Royce Deutschland BR700-715B130](https://openairdocs.org/engine/rolls-royce-deutschland-br700-715b130): 1 aircraft (registry code 54007) - [Rolls-Royce Deutschland BR700-715C130](https://openairdocs.org/engine/rolls-royce-deutschland-br700-715c130): 1 aircraft (registry code 54008) - [BMW Rolls BR700-715B130](https://openairdocs.org/engine/bmw-rolls-br700-715b130): 0 aircraft (registry code 09498) --- 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.