# TCDS E00057EN: Rolls-Royce Deutschland Ltd & Co KG - Type: Type certificate data sheet - Status: Current - Holder: Rolls-Royce Deutschland Ltd & Co KG - Revision: 13 - Revised: May 16, 2025 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 1,005, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/fb/78/fb785f07e1ba96452aa0daa2445f6e906aa8b3399a824caa88983f98b3f3473a - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID129673032920250710205334.0001 - Page: https://openairdocs.org/tcds/E00057EN ## Models (5) As the data sheet lists them. - BR700-710A2-20 - BR700-710C4-11 - BR700-725A1-12 - BR700-710A1-10 - BR700-710D5-21 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00057EN) 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 Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH) Eschenweg 11 D-15827 Dahlewitz Germany I. MODELS BR700- 710A1-10 BR700- 710A2-20 BR700- 710C4-11 BR700- 725A1-12 BR700- 710D5-21 TYPE Two spool axial flow engine consisting of a single stage fan, a ten stage axial flow compressor, an annular combustion chamber, a two stage axial flow high pressure turbine, a two/three* stage low pressure turbine, an accessory gearbox, a thrust reverser** and a Full Authority Digital Engine Control (FADEC) *BR700-710A1-10, BR700-710A2-20, BR700-710C4-11 feature a two stage axial flow low pressure turbine. BR700-725A1-12 and BR700-710D5-21 feature a three stage axial flow low pressure turbine ** BR700-725A1-12 is designed for use with a Thrust reverser, but it is not part of the engine Type Design. RATINGS (See NOTE 1) Maximum Continuous Thrust lbf/kN (See NOTE 13) Take-off Thrust, lbf/kN (See NOTE 13) 14,450/64.3 14,750/65.6 14,450/64.3 14,750/65.6 14,450/64.3 15,385/68.4 14,975/66.6 16,900/75.2 14,250/63.4 15,250/67.8 TYPE DESIGN DEFINITION DIS 10002 Issue 03 or later approved issues DIS 10005 Issue 02 or later approved issues DIS 10012 Issue 01 or later approved issues DIS 10016 Issue 03 or later approved issues DIS 10018 Issue 04 or later approved issues PAGE 1 2 3 4 5 6 7 8 9 10 REV. 13 12 11 11 13 12 11 11 11 13 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 E00057EN TCDS NUMBER E00057EN REVISION 13 DATE: May 16, 2025 Rolls-Royce Deutschland Ltd & Co KG MODELS: BR700-710A1-10 BR700-710D5-21 BR700-710A2-20 BR700-710C4-11 BR700-725A1-12 TCDS E00057EN PAGE 2 I. MODELS (cont’d) BR700- 710A1-10 BR700- 710A2-20 BR700- 710C4-11 BR700- 725A1-12 BR700- 710D5-21 EQUIPMENT E-TR150/95- (FR), issues 03 ‘Engine Equipment Classification’ or later approved issues E-TR427/96- (FR), issue 01 ‘Engine Equipment Classification’ or later approved issues E-TR466/01- (FR), issue 01 ‘Engine Equipment Classification’ or later approved issues See Installation Manual O-TR1458/08 or later approved issues See Installation Manual EDNS 01000373100/ 006 or later approved issues OVERALL DIMENSIONS (mm/in) Length Diameter 4669/183.8 1820/71.6 4669/183.8 1820/71.6 4660/183.5 1785/70.3 3297/129.8* 950/37.4** 4809/189.3† 980/38.6†† *Tip of spinner to rear of exhaust cone **Radius from centerline to the lowest point of AGB †Tip of spinner to rear of thrust reverser ††Radius from centerline to the drains plate WEIGHT (DRY) (kg/lbs) 1851.2/4081.2 1891/4168.9 1818.4/4008.9 1635.2/3605.0 1828.8/4031.8 CERTIFICATION BASIS Airworthiness Standards: BR700-710A1-10, BR700-710A2-20, BR700-710C4-11: 14 CFR part 33, effective February 1, 1965, Amendments 33-1 through 33-15, 14 CFR 33.76 Amendment 33-20 and 14 CFR 33.78 Amendment 33-19. BR700-725A1-12: 14 CFR part 33, effective February 1, 1965, Amendments 33-1 through 33-20. BR700-710D5-21: 14 CFR part 33, effective February 1, 1965, Amendments 33-1 through 33-34, except the thrust reverser unit. 14 CFR part 33, effective February 1, 1965, Amendments 33-1 through 33-15, for the thrust reverser unit. An Equivalent Level of Safety Finding has been made for the following regulation: • 14 CFR 33.78(a)(1) Large Hailstone Ingestion (documented in ELoS memo AT03470EN-E-P-5) Environmental Standards: The BR700-710A1-10 complies with 14 CFR part 34, original issue, dated September 10, 1990. The following models comply with 14 CFR part 34, Amendment 7A, effective May 24, 2024. See Note 11 for detailed summary of the certification basis for fuel venting and exhaust emissions: BR700-710A2-20, BR700-710C4-11, BR700-725A1-12 and BR700-710D5-21. MODEL APPLICATION DATE TYPE CERTIFICATE ISSUED TYPE CERTIFICATE CANCELLED BR700-710A1-10 Oct. 05, 1993 Sept. 16, 1996 BR700-710A2-20 Sept. 07, 1994 Aug. 1, 1997 BR700-710C4-11 Feb.28, 2001 June 26, 2002 BR700-725A1-12 August 2, 2007 December 16, 2009 BR700-710D5-21 Sept. 27, 2013 December 20, 2019 TCDS E00057EN PAGE 3 NOTE 1. The ratings are defined at sea level ISA standard day conditions and 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 2. Temperature Limits BR700- 710A1-10 BR700- 710A2-20 BR700- 710C4-11 BR700- 725A1-12 BR700- 710D5-21 Turbine Gas Temperature (Trimmed) oC/oF Take-off (See NOTE 13) 900/1652 900/1652 890/1634 Take-off (transient 2 mins) Maximum Continuous 860/1580 885/1625 900/1652 850/1562 Maximum over temperature (20 sec.) 905/1661 920/1688 915/1679 Maximum prior to start on ground 150/302 150/302 150/302 Starting on ground 700/1292 700/1292 700/1292 Starting in flight 850/1562 850/1562 850/1562 Oil temperatures (oC/oF) Minimum for Starting -30/-22 -40/-40 -30/-22 -40/-40 -40/-40 Minimum for Acceleration for take-off 20/68 Maximum 160/320 Fuel Temperatures (oC/oF) Minimum inlet temp. Within the T/O envelope -40/-40 Outside the T/O envelope -45/-49 Maximum inlet temp. At Sea level 54/129 At 51,000 ft 47/117 Between sea level and 51,000 ft. linear interpolation between the temperature for sea level and 51,000 ft . NOTE 3. Fuel and Oil Pressure Limits BR700-710A1-10, BR700-710A2-20, BR700-710C4-11, BR700-725A1-12 and BR700-710D5-21 Fuel Pressure Minimum permissible fuel pressure at LP fuel pump inlet: 34.5 kPa/5.0 psig Differential Oil Pressures: Minimum Acceptance for Flight in the Range: Idle to 72.3% N2: 241.2 kPa/35 psid 72.3% N2 to 90% N2: straight line interpolation from 241.2 kPa/35 psid to 310.3 kPa/45 psid Above 90% N2: 310.3 kPa/45 psid Minimum to Complete Flight: Idle to 72.3% N2: 172.3 kPa/25 psid 72.3% N2 to 90% N2: straight line interpolation from 172.3 kPa/25 psid to 241.2 kPa/35 psid Above 90% N2: 241.2 kPa/35 psid NOTES TCDS E00057EN PAGE 4 NOTE 4. Accessory Drive Provisions For BR700-710A1-10: 1) Dedicated Generator (PMA) 2) Air Turbine Starter For BR700-710A2-20: Direction* of Rotation Transmission Ratio Torque Nm (in-lbf) Weight kg (lbs) Static Overhang Moment Nm (in-lbf) Maximum Power Extraction kW (hp) Main Engine Fuel Pump including Fuel Metering Unit CW 0.530 267.0 (2363) 20.5 (45.2) 39.545 (350) 26.9 (36.1) Hydraulic Pump CCW 0.335 305.1 (2700) 6.57 (14.5) 6.1 (54) 10.3 (13.8) Generator No. 1 CW 1.083 283.0 (2505) 20.0 (44.2) 32.5 (287.6) 52 (69.7) Generator No. 2 CCW 1.080 283.0 (2505) 20.0 (44.2) 32.5 (287.6) 52 (69.7) Generator FADEC1 CW 1.998 1.0 (2.2) 1.0 (8.85) 1.0 (1.34) Starter2 CCW 0.986 847.0 (7497) 15.56 (34.3) 22.7 (201) Oil Pump CCW 0.421 51.8 (458) 9.07 (20) 6.6 (58.4) 3.2 (4.3) *CW: clockwise; CCW: counterclockwise, looking normal to pad along shaft 1) Dedicated Generator (PMA) 2) Air Turbine Starter Direction* of Rotation Transmission Ratio Torque Nm (in-lbf) Weight kg (lbs) Static Overhang Moment Nm (in-lbf) Maximum Power Extraction kW (hp) Main Engine Fuel Pump including Fuel Metering Unit CW 0.530 267.0 (2363) 20.5 (45.2) 39.545 (350) 26.9 (36.1) Hydraulic Pump No. 1 CCW 0.270 418.0 (3700) 8.91 (19.64) 8.1 (71.7) 18.6 (24.9) Hydraulic Pump No. 2 CCW 0.275 418.0 (3700) 8.91 (19.64) 8.1 (71.7) 18.6 (24.9) Generator CW 0.520 412.5 (3651) 32.61 (71.9) 56.492 (500) 32.7 (43.9) Generator FADEC1 CW 1.998 1.0 (2.2) 1.0 (8.85) 1.0 (1.34) Starter2 CCW 0.986 847.0 (7497) 15.56 (34.3) 22.7 (201) Oil Pump CCW 0.408 51.8 (458) 9.07 (20) 6.6 (58.4) 3.2 (4.3) *CW: clockwise; CCW: counterclockwise, looking normal to pad along shaft TCDS E00057EN PAGE 5 NOTE 4 continued. Accessory Drive Provisions For BR700-710C4-11: For BR700-725A1-12: Direction* of Rotation Transmission Ratio Shear Torque Nm (in-lbf) Weight kg (lbs) Dry Static Overhang Moment Nm (in-lbf) Contin. Torque Extraction Nm (in-lbf) Hydraulic Pump CW 0.261 406.75 14.82*** 16.37 120 (1062)** (3600) (32.67) Generator CW 0.522 412.5 32.61 56.5 109 (965)** (IDG) (3651) (71.9) Air Turbine CW 0.988 847 9.99 6.76 415 (3673) Starter (ATS) (7497) (22.0) *CW: clockwise; CCW: counterclockwise, looking normal to pad along shaft ** Further details regarding acceptable loading are defined in the Installation Manual *** WET For BR700-710D5-21: Direction* of Rotation Gear Ratio To N2 Ratio Shear Neck Value Nm (in-lbf) Weight kg (lbs) Dry Max wet Overhung Moment Nm (in-lbf) Maximum. Torque** Nm (in-lbf) EDP CCW 0.2778 305.1 8.48 9.5 (84) 50.8 (4496) (2700) (18.7) Variable CCW 0.8594 293 20.29 22.03 (195) 50.0 (443) Frequency (2593) (44.7) Generator highest (VFG) Pad 1, 4 VFG CW 0.8978 293 20.29 22.03 (195) 50.0 (443) Pad 2, 3 (2593) (44.7) highest *CW: clockwise; CCW: counterclockwise, looking normal to pad along shaft ** Further details regarding acceptable loading are defined in the Installation Manual NOTE 5. Model Description BR700-710A1-10 Baseline engine configuration BR700-710A2-20 Same as BR700-710A1-10 except for a different airplane application BR700-710C4-11 Same as BR700-710A1-10 except for higher ratings BR700-725A1-12 Same as BR700-710A1-10 except for increased fan diameter and additional stage on the LP Turbine and a higher rating. Thrust reverser is not included in engine type design BR700-710D5-21 Same as BR700-710A1-10 except for improved HP system and additional stage on the LP turbine with an optimized rating. NOTE 6. Typical Aircraft Accessories, Components, Or System Assemblies, With Aircraft Level Requirements, Provided As Part Of Engine Type Design: The thrust reverser (see Note 11) is provided with the engine and is part of the engine type design, except for the BR700- 725A1-12 engine model. Direction* of Rotation Transmission Ratio Torque Nm (in-lbf) Weight kg (lbs) Static Overhang Moment Nm (in-lbf) Maximum Power Extraction kW (hp) Hydraulic Pump CCW 0.275 418.0 8.91 8.1(71.7) 18.6(24.9) No. 2 (3700) (19.64) Generator CW 0.520 412.5 32.61 56.5 (500) 32.75(43.9) (IDG) (3651) (71.9) *CW: clockwise; CCW: counterclockwise, looking normal to pad along shaft TCDS E00057EN PAGE 6 NOTE 7. Aircraft Accessories, Components, Or System Assemblies Installed On The Engine But Are Not Provided As Part Of Engine Type Design: Not Applicable NOTE 8. Special Anti-Icing Or De-Icing Requirements: Not Applicable NOTE 9. Engine Mount System Provisions: Not Applicable NOTE 10. Power Boost, Injection Or Augmentation Systems: Not Applicable NOTE 11. Special Installation Requirements: ETOPS: Not approved for ETOPS operations THRUST REVERSER: The engines are approved for use with a thrust reverser: BR700-710A1-10: P/N 04G0001-039 (left hand engine) and P/N 04G0001-041 (right hand engine) or later approved standards. BR700-710A2-20: P/N 07G0001-005 (left hand engine) and P/N 07G0001-007 (right hand engine) or later approved standards. BR700-710C4-11: P/N 25G0001-001 (left hand engine) and P/N 25G0001-003 (right hand engine) or later approved standards. BR700-725A1-12: P/N RD00103001-1 (left hand engine) and P/N RD00103001-2 (right hand engine) or later approved standards. BR700-710D5-21: P/N 29G0001-021 (left hand engine) and P/N 29G0001-023 (right hand engine) or later approved standards. Operation of these thrust reversers is approved for ground use only. Use for power back is not approved. The thrust reverser is part of the engine type design, except for the BR700-725A1-12 EXHAUST EMISSIONS AND FUEL VENTING: The following emissions standards promulgated in 14 CFR part 34, Amendment 7A, effective May 24, 2024, and 40 CFR part 1031, effective December 23, 2022, have been complied with for: BR700-710A2-20, BR700-710C4-11, BR700-725A1-12, and BR700-710D5-21. • Fuel Venting Emission Standards: 14 CFR §§ 34.10(a) and 34.11; in addition, 40 CFR 1031.30(b). • Smoke Number (SN) Emission Standards: 14 CFR 34.21(e)(2); in addition, 40 CFR 1031.60(a)(5). • Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 1031.60(d). • Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 1031.60(c). • Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(b)(1); in addition, 40 CFR 1031.60(e)(5). • non-volatile Particulate Matter (nvPM) Mass Concentration Emission Standards: 14 CFR 34.25(a)(1) and 40 CFR 1031.60(a)(6) (Tier 10) • nvPM Mass and Number Emission Standards: 14 CFR 34.25(a)(2) and 40 CFR 1031.60(b)(2) (Tier 11 in- production) In addition to the FAA’s finding of compliance based on the certification requirements defined in this TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Fourth Edition, Part III, Chapter 2, Section 2.2.2 for SN, Section 2.3.2 for CO and HC, Section 2.3.2.e for NOx (also known as CAEP/8), Chapter 4, Section 4.2.2.1 for nvPM Mass Concentration (CAEP/10), Section 4.2.2.2 for nvPM Mass and Number (CAEP/11), and Part II Chapter 2 for fuel venting, have also been demonstrated. TIME LIMITED DISPATCH: The engine models are approved for Time Limited Dispatch. Information on engine operation with FADEC system dispatch limitations is contained in the respective Engine Operating Instructions, Airworthiness Limitations Section of the Time Limits Manuals and the following reports: BR700-710A1-10: Report E-TR361/96 (FR) Issue 00 or later approved issues BR700-710A2-20: Report E-TR737/96 (FR) Issue 1 or later approved issues BR700-710C4-11: Report E-TR080/02-(FR)-ISS01, or later approved issues TCDS E00057EN PAGE 7 ELECTROMAGNETIC PROTECTION: Lightning and EMI protection capability of the electronic engine control system, are specified in the Installation Manual, see NOTE 15. NOTE 12. Service Bulletins Or Other Instructions For Matters Of Special Interest: Not applicable NOTE 13. Special Operating Procedures Or Limitations Use of take-off 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 14. Special repair or overhaul limitations: Not Applicable NOTE 15. Operating and Service Instructions: BR700-710A1-10 BR700-710A2-20 Installation Drawing and Manual E-TR206/95 Issue 6 E-TR364/95 Issue 1 or later approved issues or later approved issues Operating Instructions OI-710-1BR OI-710-2BR Maintenance Manual M-710-1BR M-710-2BR Engine Manual E-710-1BR E-710-2BR Time Limits Manual T-710-1BR T-710-2BR BR700-710C4-11 BR700-725A1-12 Installation Drawing and Manual E-TR240/01-(FR)-ISS01 O-TR1458/08 Issue 2 or later approved issues or later approved issues Operating Instructions OI-710-4BR OI-725-7BR Maintenance Manual M-710-4BR M-725-7BR Engine Manual E-710-4BR E-725-7BR Time Limits Manual T-710-4BR T-725-7BR BR700-710D5-21 Installation Drawing and Manual EDNS 01000373100/008 or later approved issues. Operating Instructions OI-710-8BR Maintenance Manual M-710-8BR Engine Manual E-710-8BR Time Limits Manual T-710-8BR Service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals which contain a statement that the document is EASA approved are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only NOTE 16. Import Requirements: To be considered for installation on United States registered aircraft, each engine to be exported to the United States shall be accompanied by a certificate of airworthiness for export, or certifying statement endorsed by the exporting cognizant civil airworthiness authority, which contains the following language: These engines conform to the United States type design (Type Certificate Number E00057EN) and are in a condition for safe operation. These engines have been subjected by the manufacturer to a final operational check and are in a proper state of airworthiness. Reference 14 CFR 21.500, which provides for the airworthiness acceptance of aircraft engines or propellers manufactured outside of the United States for which a United States type certificate has been issued. 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. TCDS E00057EN PAGE 8 NOTE 17. Life Limited Part Information: Life limited critical parts are included in the respective Time Limits Manual, see NOTE 15. NOTE 18. Military model information: Not applicable NOTE 19. Maximum Rotational Speeds: BR700- 710A1-10 BR700- 710A2-20 BR700- 710C4-11 BR700- 725A1-12 BR700- 710D5-21 Low Pressure Turbine N1 (%) -Maximum Take-off (See NOTE 13) -Maximum Continuous -Maximum Overspeed (20 sec.) -Reverse Thrust (max. 30 sec.) -Acceleration to Takeoff with Cross Winds above 20 kts -Stabilized engine operation is not approved for aircraft static on the ground 101.1 101.0 101.5 70 66* between 66 and 80** 102.1 102.1 102.5 70 66* between 66 and 80** 101.1 101.0 101.5 70 66* between 66 and 80** 102.8 102.8 104.3 78.1 Refer to Operating Instructions OI-725-7BR 102.1 102.1 103.3 70.4 Refer to Operating Instructions OI-710-8BR High Pressure Turbine N2 (%) -Maximum Take-off (See NOTE 13) - Maximum Continuous -Maximum Overspeed (20 sec.) 99.6 98.9 99.8 99.6 98.9 99.8 99.6 98.9 99.8 100.0 98.7 101.3 101.6 99.9 102.8 *Until a forward speed of 20 kts is reached. Above 20 kts forward speed, a slam acceleration to take-off is required. ** Acceleration or deceleration through this band must not exceed 10 seconds (forward thrust only). BR700-710A1-10, BR700-710-A2-20, BR700-7104-11: 100% N1 equals 7431 RPM, 100% N2 equals 15898 RPM BR700-725A1-12: 100% N1 equals 7000 RPM, 100% N2 equals 15898 RPM BR700-710D5-21: 100% N1 equals 7431 RPM, 100% N2 equals 19000 RPM NOTE 20. Output/Propeller Shaft Torque Limit: Not Applicable NOTE 21. Bleed Air Extraction: For BR700-710A1-10, BR700-710A2-20, BR700-710C4-11 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 fan entry mass flow, W1A. For BR700-710A1-10: Power Range Normal Flow (%) Maximum Flow (%) Stage 5 Stage 8 Fan Stage 5 Stage 8* Fan Idle to 1.06 EPR 7.8 3.0 12.1 0.6 1.06 to 1.3 EPR 4.4 4.2 0.2 8.3 7.9 1.6 Above 1.3 EPR 4.3 0.4 8.5 8.0 1.8 For BR700-710A2-20: Power Range Normal Flow (%) Maximum Flow (%) Stage 5 Stage 8 Fan Stage 5 Stage 8* Fan Idle to 1.06 EPR 7.8 0.4 3.0 12.1 0.6 1.06 to 1.3 EPR 4.4 4.2 0.4 8.3 7.9 0.9 Above 1.3 EPR 4.3 0.4 8.5 8.0 1.1 TCDS E00057EN PAGE 9 * Stage 8 bleed is cleared for operation up to and including Maximum Continuous rating. NOTE 21. Cont’d Bleed Air Extraction: For BR700-710A1-10, BR700-710A2-20, BR700-710C4-11 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 fan entry mass flow, W1A. For BR700-710C4-11: Power Range Normal Flow (%) Maximum Flow (%) Stage 5 Stage 8 Fan Stage 5 Stage 8* Fan Idle to 1.06 EPR 7.7 3.0 12.0 0.6 1.06 to 1.3 EPR 4.3 4.1 0.2 8.2 7.8 1.6 Above 1.3 EPR 4.2 0.4 8.3 7.8 1.8 *Stage 8 bleed is cleared for operation up to and including Maximum Continuous rating. For BR700-725A1-12: HP Bleed Stage 5 Nominal Maximum NHRT2 % W26 NHRT2 % W26 Idle - 675 6.5 Idle - 700 7.7 675 - 850 10.1 700 - 875 10.1 850 - MTO 6.5 875 - MTO 8.6 HP Bleed Stage 8 Nominal Maximum NHRT2 % W26 NHRT2 % W26 Idle - 790 13.6 Idle - 800 14.1 790 - MTO 9.3 800 - MTO 13.6 LP (Fan) Bleed Nominal Maximum NHRT2 % W12 NHRT2 % W12 Idle - 700 1.4 Idle - 720 1.5 700 - 775 1.7 720 - MTO 1.9 775 - MTO 1.7 For BR700-725A1-12, - Stage 5 and stage 8 HP compressor customer bleed is expressed as a percentage of HP Compressor entry mass flow W26. - Fan bleed flow is expressed as percentage of the fan tip entry mass flow W12. - Further details regarding acceptable conditions for customer bleed air extractions are defined in the installation Manual TCDS E00057EN PAGE 10 NOTE 21. Cont’d Bleed Air Extraction: For BR700-710D5-21 - Fan bleed flow is expressed as percentage of the total fan face entry mass flow W020A. - Stage 4 and stage 7 HP compressor customer bleed is expressed as a percentage of HP compressor entry mass flow W026. - A constant percentage of 1.6%W026 is supplied by HPC stage 4 bleed across the full NHRT2 range. - For NHRT2 > 980, stage 7 extraction must be zero for stage 4 extraction greater than 1.6%W026. - Further details regarding acceptable conditions for customer bleed air extractions are defined in the Installation Manual. For BR700-710D5-21: HP Bleed Stage 4 Nominal Maximum NHRT2 % W026 NHRT2 % W026 Idle - 980 1.6 Idle - 980 1.6 > 980 5.6* > 980 7.3* HP Bleed Stage 7 Nominal Maximum NHRT2 % W026 NHRT2 % W026 Idle - 980 9.9 Idle - 980 11.7 > 980 9.2 > 980 10.8 Fan Bleed Nominal Maximum NHRT2 % W020A NHRT2 % W020A Idle - 980 0.5 Idle - 980 0.5 > 980 0.6 > 980 0.6 *Stage 7 extraction must be zero for stage 4 extraction greater than 1.6%W026 NOTE 22. NOTE 23 Rotor Disk Integrity and Rotor Blade Containment (where special requirements apply) Not Applicable FADEC: BR700-710A1-10: EEC P/N 1501KDC01-817 or later approved standards. BR700-710A2-20: EEC P/N 1520KDC01-605, or later approved standards. BR700-710C4-11: EEC P/N 1505KDC01-002, or later approved standards. BR700-725A1-12: EEC P/N G3010ECU01BA or later approved standards BR700-710D5-21: EEC P/N G3020ECU01AE or later approved standards The EEC software has been developed and verified in accordance with RTCA/DO-178B respectively ED-12B Level A. NOTE 24. Approved fuels and fuel additives are listed in the latest applicable issue of the applicable engine Operating Instructions, see NOTE 15. NOTE 25. Approved oils are listed in the latest applicable issue of the applicable engine Operating Instructions, see NOTE 15. NOTE 26. The maximum permissible engine inlet distortion limit is specified in the applicable Engine Installation Manual, see NOTE 15. TCDS E00057EN PAGE 11 NOTE 27. The BR700-725A1-12 engine is approved for ground operation in freezing fog conditions down to an ambient temperature of -20 °C. ---THE END--- ``` ## ADs (18, in force first) - [AD 2025-06-03](https://openairdocs.org/ad/2025-06-03): Turbine Engine Compressor Section · Rolls-Royce Deutschland BR700-710A1-10, BR700-710A2-20 and BR700-710C4-11. Effective Apr 23, 2025 - [AD 2022-26-02](https://openairdocs.org/ad/2022-26-02): Accessory Gearboxes · Rolls-Royce Deutschland BR700-710A1-10, BR700-710A2-20, BR700-710C4-11 and 1 more. Effective Jan 27, 2023 - [AD 2021-21-12](https://openairdocs.org/ad/2021-21-12): Turbine Engine Compressor Section · Rolls-Royce Deutschland BR700-710A2-20. Effective Dec 13, 2021 - [AD 2021-12-07](https://openairdocs.org/ad/2021-12-07): Turbine Engine Compressor Section · Rolls-Royce Deutschland BR700-710A1-10, BR700-710A2-20 and BR700-710C4-11. Effective Aug 12, 2021 - [AD 2018-18-14](https://openairdocs.org/ad/2018-18-14): Engine Controls · Rolls-Royce Deutschland BR700-710A2-20 and BR700-710C4-11. Effective Oct 12, 2018 - [AD 2016-13-12](https://openairdocs.org/ad/2016-13-12): Pawl carrier pivot pins · Rolls-Royce Deutschland BR700-710A1-10, BR700-710A2-20 and BR700-710C4-11. Effective Aug 5, 2016 - [AD 2014-12-03](https://openairdocs.org/ad/2014-12-03): Fuel metering units (FMUs) · Rolls-Royce Deutschland BR700-725A1-12. Effective Jul 17, 2014 - [AD 2013-12-03](https://openairdocs.org/ad/2013-12-03): Fuel pump tube · Rolls-Royce Deutschland BR700-725A1-12. Effective Jun 14, 2013 - [AD 2013-03-17](https://openairdocs.org/ad/2013-03-17): High-pressure turbine (HPT) stage 1 and stage 2 discs · Rolls-Royce Deutschland BR700-710A1-10, BR700-710A2-20 and BR700-710C4-11. Effective Mar 21, 2013 - [AD 2011-22-01](https://openairdocs.org/ad/2011-22-01): Touch-and-go and overshoot on life cycle counting · Rolls-Royce Deutschland BR700-710A1-10, BR700-710A2-20 and BR700-710C4-11. Effective Nov 23, 2011 - [AD 2010-25-05](https://openairdocs.org/ad/2010-25-05): Turbine Discs · Rolls-Royce Deutschland BR700-710A1-10, BR700-710A2-20 and BR700-710C4-11. Effective Jan 13, 2011 - [AD 2005-21-05](https://openairdocs.org/ad/2005-21-05): Fan discs and fan blades · Rolls-Royce Deutschland BR700-710A1-10 and BR700-710A2-20. Effective Nov 25, 2005 - [AD 2001-01-01](https://openairdocs.org/ad/2001-01-01): Oil Filter · Rolls-Royce Deutschland BR700-710A1-10 and BR700-710A2-20. Effective Jan 31, 2001 - [AD 98-24-03 R1](https://openairdocs.org/ad/98-24-03-R1): Combustion Core Fairings · Rolls-Royce Deutschland BR700-710A1-10 and BR700-710A2-20. Effective Dec 27, 1999 - [AD 2022-24-06](https://openairdocs.org/ad/2022-24-06) (historical): Turbine Engine Compressor Section · Rolls-Royce Deutschland BR700-710A1-10, BR700-710A2-20 and BR700-710C4-11. Effective Jan 6, 2023 - [AD 2013-05-13](https://openairdocs.org/ad/2013-05-13) (historical): Fuel pump splined couplings · Rolls-Royce Deutschland BR700-710A1-10, BR700-710A2-20 and BR700-710C4-11. Effective Apr 24, 2013 - [AD 2003-07-11](https://openairdocs.org/ad/2003-07-11) (historical): Fan discs · Rolls-Royce Deutschland BR700-710A1-10 and BR700-710A2-20. Effective Apr 28, 2003 - [AD 2001-05-06](https://openairdocs.org/ad/2001-05-06) (historical): Fan Disk · BMW Rolls-Royce BR700-710A1-10 and BR700-710A2-20. Effective Mar 29, 2001 ## Registered aircraft by registry model (OpenAirDocs) - [Rolls-Royce Deutschland BR700-710C411](https://openairdocs.org/engine/rolls-royce-deutschland-br700-710c411): 292 aircraft (registry code 54005) - [Rolls-Royce Deutschland BR700-710A220](https://openairdocs.org/engine/rolls-royce-deutschland-br700-710a220): 273 aircraft (registry code 54004) - [Rolls-Royce Deutschland BR700-725A112](https://openairdocs.org/engine/rolls-royce-deutschland-br700-725a112): 260 aircraft (registry code 54231) - [Rolls Deu BR700-710D521](https://openairdocs.org/engine/rolls-deu-br700-710d521): 88 aircraft (registry code 54607) - [BMW Rolls BR700-710C411](https://openairdocs.org/engine/bmw-rolls-br700-710c411): 35 aircraft (registry code 09494) - [BMW Rolls BR700-710A220](https://openairdocs.org/engine/bmw-rolls-br700-710a220): 27 aircraft (registry code 09495) - [Rolls-Royce Deutschland BR700-710A110](https://openairdocs.org/engine/rolls-royce-deutschland-br700-710a110): 22 aircraft (registry code 54003) - [BMW Rolls BR700-710A110](https://openairdocs.org/engine/bmw-rolls-br700-710a110): 8 aircraft (registry code 09496) --- 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.