TCDS E00099EN

PAGE 1 2 3 4 5 6 REV. 1 1 1 1 1 1 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 E00099 EN TCDS NUMBER E00099EN REVISION 1 DATE: November 24, 2023 Rolls-Royce Deutschland Ltd & Co KG MODELS: BR700-730B2-14 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E000 99EN) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft i n 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 Blankenfelde-Mahlow Germany I. MODELS BR700-730B2-14 TYPE Two spool axial flow engine consisting of a sin gle stage fan, a ten stage axial flow compressor, an annular combustion chamber, a two stage axial flow high pressure turbine, a four stage axial flow low pressure turbine, an accesso ry gearbox, and a Full Authority Digital Engine Control (FADEC). TYPE DESIGN DEFINITION DIS 10022 Issue 01 Revision Y,plus Modifications provided in Chapte r 3 of EDNS01001075067/002-Iss02, or later approved issues I. MODELS (cont’d) BR700-730B2-14 EQUIPMENT The engine starter and starter air valve are part of the engine type design. For details of equipment included in the Type Design definition refer to the Engine Drawing Introduction Sheet. The Thrust Reverser Unit is not part of the engine type design. OVERALL DIMENSIONS (mm/in) Length* Radius** 3268/128.7 988/38.9 *Tip of spinner to rear of exhaust cone **Radius from centerline to the lowest point of AGB RATINGS (See NOTE 1) Maximum Continuous Thrust lbf/kN (See NOTE 13) Take-off Thrust, lbf/kN (See NOTE 13) 16,220/72.2 18,250/81.2 TCDS E00099EN PAGE 2 WEIGHT (DRY) (kg/lbs) 1617.1/3565.1 CERTIFICATION BASIS Airworthiness Standards: 14 CFR, Part 33, effective February 1, 1965, as amended by 33 -1 through 33-34 Exemptions have been granted from the following regulations: 14 CFR 33.27(f)(6) to the extent necessary to allow RRD to exclude the interstage drive -arm, connecting the stage 1 disk of the High Pressure Turbine (HPT) to the stage 2 disk of the HPT in the High Pressure (HP) shaft system (documented in Exemption No. 19989) 14 CFR 33.27(c) to the extent necessary to allow RRD to exclude the integral disk drive arm connecting the flange of the low-pressure shaft to the stage 3 disk (documented in Exemption No. 20473) Environmental Standards : 14 CFR, Part 34, Amendment 34 -6, effective March 6, 2018 See Note 11 for detailed summary of the certification basis for fuel venting and exhaust emissions. MODEL APPLICATION DATE TYPE CERTIFICATE ISSUED TYPE CERTIFICATE CANCELLED BR700-730B2-14 Feb 23, 2018* August 16, 2023 *FAA accepted validation program extension requested April 26, 2021. NOTES NOTE 1. Engine Ratings Engine ratings are based on calibrated stand performance under standard day conditions At sea level static the engine is flat rated at a constant thr ust of 81.2 kN (18250 lbf) up to the kink point at ISA + 12 Kelvin. NOTE 2. Temperature Limits Turbine Gas Temperature (Trimmed) oC/oF Take-off (See NOTE 13) 940/1724 Take-off (transient 2 mins) Maximum Continuous 950/1742 940/1724 Maximum over temperature (20 sec.) 960/1760 Maximum prior to start on ground 120/248 Starting on ground 800/1472 Starting in flight 850/1562 Oil temperatures ( oC/oF) Minimum for starting -36/-33 Minimum for acceleration for take-off 20/68 Maximum 170/338 Maximum transient limit 175/347 Fuel Temperatures (oC/oF) Minimum LP pump inlet temp. Within the T/O envelope Outside the T/O envelope -40/-40 -40/-40 Maximum LP pump inlet temp. At sea level At 51,000 ft Between sea level and 51,000 ft. 54/129 47/117 linear interpolation between the temperature for sea level and 51,000 ft TCDS E00099EN PAGE 3 NOTE 3. Fuel and Oil Pressure Limits Fuel Pressure Minimum permissible fuel pressure at LP fuel pump inlet: -2000 feet Sea level: 10,000 feet: 51,000 feet: true vapor pressure + 16 psia (true vapor pressure + 110.3 kPa) true vapor pressure + 15 psia (true vapor pressure + 103.4 kPa) true vapor pressure + 10 psia (true vapor pressure + 68.9 kPa) true vapor pressure + 5 psia (true vapo r pressure + 34.5 kPa) The minimum fuel pressure at the low pressure fuel pump inlet between stated altitudes are derived by linear interpolation between the values given for adjacent stated altitudes. Differential Oil Pressures: Minimum acceptance for flight in the range: Idle to 72.3% N2: 72.3% N2 to 90% N2: Above 90% N2: Minimum to complete flight: Idle to 72.3% N2: 72.3% N2 to 90% N2: Above 90% N2: 241.2 kPa/35 psid straight line interpolation from 241.2 kPa/35 psid to 310.3 kPa/45 psid 310.3 kPa/45 psid 172.3 kPa/25 psid straight line interpolat ion from 172.3 kPa/25 psid to 241.2 kPa/35 psid 241.2 kPa/35 psid NOTE 4. Accessory Drive Provisions Direction* of Rotation Transmission Ratio Torque Nm (in-lbf) Weight kg (lbs) Static Overhang Moment Nm (in-lbf) Continuous Power Extraction** Nm (in-lbf) Hydraulic Pump CW 0.261 406.75 (3600) 13.2 (29) 16.37 (155) 120 (1062) IDG (Generator) CW 0.522 412.5 (3651) 29.5 (65) 56.5 (500) 100 (885.1) *CW: clockwise; facing the appropriate gearbox drive pad. ** Further details regarding acceptable loading are defined in the Installation Requirements Document. NOTE 5. Model Description BR700-730B2-14 Baseline engine configuration NOTE 6. Typical Aircraft Accesso ries, Components, Or System Assemblies, With Aircraft Level Requirements, Provided As Part Of Engine Type Design: Not Applicable TCDS E00099EN PAGE 4 NOTE 7. Aircraft Accessories, Compo nents, Or System Assemblies Installed On The Engine But Are Not Provided As Part Of Engine Type Design: The Thrust Reverser Unit is not part of the engine type design. The engines are equipped with a thrust reverser (which is not part of the engine design) with the following part numbers: Left hand engine BNL4000-53-0 Right hand engine BNL6000-53-0 Operation of these thrust reversers is ap proved for ground use only. Use for power back is not approved. 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 fo r use with a thrust reverser; see NOTE 7. EXHAUST EMISSIONS AND FUEL VENTI NG: The following emissions standards promulgated in 14 CFR part 34, Amendment 6, effective March 6, 2018, an d 40 CFR part 1031, effective November 23, 2022, have been complied with for: Fuel Venting Emission Standards: 14 CFR §§ 34.10(a) and 34.11; in addition, 40 CFR §§ 87.10(a) and 87.11. 14 CFR §34.60 Introduction and 40 CFR §1031.30. Smoke Emission Standa rds: 14 CFR §34.21(e)(2); in addition, 40 CFR §1031.60(a)(5) Tier 1 superseded since 1.1.23 by 40 CFR §1031.60(a)(6) Tier 1 0 mass concentration, and 4 0 CFR §1031.60(b) LTO nvPM mass and number (1) Tier 11 new type and (2) Tier 11 in -production. Hydrocarbons (HC) Emission Standard: 14 CFR §34.21(d)(1)(i); in addition, 40 CFR §1031.60(c). Carbon Monoxide (CO) Emission Standard: 14 CFR §34.21(d)(1)(ii); in addition, 40 CFR §1031.60(d). Oxides of Nitrogen (NOx) Emission Standards: 14 CFR §34.23(a)(2) Tier 6 and 14 CFR §34.23(b)(1) Tier 8; in addition, 40 CFR §1031.60(e)(4) Tier 6 and 40 CFR §1031.60(e)(5) Tier 8.” In addition to the FAA’s finding of complian ce based on the certification requirements defined in this TCDS, the engine manufacturer has declared that th e ICAO emissions standards identified in ICAO Annex 16 Volume II (Fourth Edition, 2017 Amendment 10), 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 for nvPM ( CAEP/10 and 11), and Part II Chapter 2 for fuel venting have also been demonstrated. TIME LIMITED DISPATCH: Information on engine operation with FADEC system dispatch limitations is contained in the respective Engine Operating Instructions and Time Limits Manuals. ELECTROMAGNETIC PROTECTION : Information on lightning pro tection and electromagnetic compatibility is contained in the Installation Requirements Document; see NOTE 15. NOTE 12. Service Bulletins Or Other Instructions For Matters Of Special Interest: See NOTE 15 for service bulletin and other service instruction information. TCDS E00099EN PAGE 5 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. The BR700-730B2-14 engine is approved for ground operation in freezing fog conditions down to an ambient temperature of -20°C/-4˚F. If at time of dispatch an engine-independent source of starter air pressure is not available (e.g. A PU is inoperable), the ceiling altitude for aircraft operation shall be restricted to 30,000 feet. NOTE 14. Special repair or overhaul limitat ions: Not Applicable NOTE 15. Operating and Service Instructions: Engine Installation Requirements Document EDNS01000951368/008-Iss008 or later approved issues Operating Instructions OI-730-9BR Maintenance Manual M-730-9BR Engine Manual E-730-9BR Time Limits Manual T-730-9BR Component Maintenance Manuals Various Service bulletins, structural repair m anuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals which contain a statement that the document is EASA ap proved 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 St ates registered aircraft, each engine to be exported to the Un ited States shall be accompanied by a certificate of airwort hiness for export, or certifying statement endorsed by t he exporting cognizant civil airworthiness authority, which contains the follo wing language: These engines conform to the United States typ e design (Type Certificate Number E00099EN) and are in a condition for safe operation. These engines have been subj ected by the manufacturer to a final oper ational check and are in a proper sta te of airworthiness. Reference 14 CFR 21.500, which provides for the airworthiness acceptance of aircraft engines or prop ellers manufactured outside of the United States for whi ch a United States type certificate has b een issued. Additional guidance is c ontained in FAA Advisory Circular 21 -23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products, imported into the United States. NOTE 17. Life Limited Part Information: Life limited critical parts are included in th e respective Time Limits Manual; see NOTE 15. NOTE 18. Military model informatio n: Not Applicable TCDS E00099EN PAGE 6 NOTE 19. Maximum Rotational Speeds: BR700-730B2-14 Low Pressure Turbine N1 (%) : -Maximum Take-off (See NOTE 13) -Maximum Continuous -Maximum Overspeed (20 sec.) -Reverse Thrust (max. 30 sec.) 96.6 96.6 97.8 73.1 High Pressure Turbine N2 (%): -Maximum Take-off (See NOTE 13) - Maximum Continuous -Maximum Overspeed (20 sec.) 102.2 102.2 103.4 100% N1 (NL) equals 6500 RPM; 100% N2 (NH) equals 19000 RPM NOTE 20. Output/Propeller Shaft Torque Lim it: Not Applicable NOTE 21. Bleed Air Extraction: Nominal Flow kg/s(lb/s) Maximum Flow kg/s(lb/s) Bleed Stage HPC Stage 4 HPC Stage 7 Fan HPC Stage 4 HPC Stage 7 Fan Flow 1.54(3.4) 1.41(3.1) 4.40(9.7) 2.27(5.0) 2.36(5.2) 4.45(9.8) NOTE 22. NOTE 23 Rotor Disk Integrity and Rotor Blade Containment (where special requirements appl y) Not Applicable FADEC: The engine is equipped with a Full Authority Digital Engine Control (FADEC) system. Refer to the Engine Installation Requirements Document and Operating Instructions for further information; see NOTE 15. EEC P/N T3030ECU02 or later approved standards. Software P/N RRY57FLC0A04002 or later approved standards. The EEC software ha s been developed and verified in accordance with RTCA/DO-178C respectively ED-12C Level A, with development assurance carried out in accordance with ED79A/ARP4754A. NOTE 24. Approved fuels and fuel additives are listed in t he latest applicable issue of the applicabl e engine Operating Instructions; see NOTE 15. NOTE 25. Approved oils are listed in the latest ap plicable issue of the applicable engine Operating Instructions; see NOTE 15. NOTE 26. The maximum permissible en gine inlet distortion limit is specified in the applicable engine Installation Requirements Document; see NOTE 15. ---THE END---