TCDS E00050EN

LEGEND: “- -“ INDICATES “SAME AS PRECEDING MODEL” “- -“ INDICATES “NOT APPLICABLE” U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHE ET E00050EN TCDS NUMBER E00050EN DATE: April 25, 2019 Revision 9 ROLLS-ROYCE, Deutschland Ltd. & Co. KG MODELS: RB211-TRENT 892-17 RB211-TRENT 875-17 RB211-TRENT 884-17 RB211-TRENT 884B-17 RB211-TRENT-892B-17 RB211-TRENT 877-17 RB211-TRENT 895-17 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00050EN) 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 Avia tion 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 Eschenweg 11, 15827 Blank enfelde-Mahlow, Germany TYPE CERTIFICATE (TC) HOLDER: Rolls -Royce, plc transferred TC E00050EN to Rolls - Royce, Deutschland on February 21, 2019 I. MODELS RB211- Trent 892-17 RB211- Trent 884-17 RB211- Trent 884B-17 RB211- Trent 877-17 RB211- Trent 875-17 RB211- Trent 892B-17 RB211- Trent 895-17 TYPE High by-pass turbofan (by-pass ratio of 6.4:1 at a typical cruise thrust) axial flow, three -rotor. Single- stage low pressure fan driven by a five -stage turbine. Eight -stage intermediate pressure compressor driven by single stage turbine. Six -stage high pressure compressor driven by single stage turbine. Annular combustion chamber. RATINGS (See NOTE 1) Maximum continuous Thrust, pounds net at sea level static Takeoff (5 minutes, see NOTE 19) Thrust, pounds net at sea level static Equivalent bare engine thrust, pounds* 77170(2) 91450(1) 92800 70210(2) 85430(1) 86700 70210(2) 85430(1) 86700 70210(2) 78910(3) 80110 62160(2) 76580(1) 77750 77170(2) 91450(4)(5) 92800 77170(2) 92940(6) 94320 1. Flat rated to ISA + 15oC at all altitudes 2. Flat rated to ISA + 10oC at all altitudes. The 884B -17 maximum continuous thrust is the same as the 884-17 rating up to 12,000ft, then increases linearly to the 892-17 maximum continuous thrust at 25,000ft and above. 3. Flat rated ISA + 22.8oC between -2000 feet and 2000 feet varying linearly to ISA + 15 oC at 5000 feet ISA + 15oC above 5000 feet. 4. Flat rated ISA + 15oC between -2000 feet and 2000 feet, then varying linearly to ISA + 4oC at 4550 feet, then varying linearly to ISA + 8oC at 6550 feet, then varying linearly to ISA + 15oC at 8000 feet. ISA + 15 oC above 8000 feet. 5. The 892B-17 provides higher take -off thrust than the 892 -17 at altitudes between 2000 feet a nd 8000 feet. The thrust increase varies with altitude, Mach number and ambient tempe - rature and is limited to a maximum of 5.2%. PAGE 1 2 3 4 5 6 7 REV. 9 3 7 8 8 7 5 TCDS E00050EN Page 2 of 7 LEGEND: “- -“ INDICATES “SAME AS PRECEDING MODEL” “- -“ INDICATES “NOT APPLICABLE” Ratings (Cont’d) 6. The 895-17 is flat rated as follows: a) Between –2000 ft and 457 ft, ISA +10 oC b) Between 457 ft and 1500 ft, varies linearly between ISA 10 oC and ISA +9oC c) Between 1500 ft and 2000 ft, varies linearly between ISA+9 oC and ISA +10oC d) Between 2000 ft and 4000 ft, varies linearly between ISA +10 oC and ISA +5oC e) Between 4000 ft and 6000 ft, ISA +5oC f) Between 6000 ft and 6550 ft, varies linearly between ISA +5 oC and ISA +10oC g) Between 6550 ft and 10000 ft, ISA +10oC h) Between 10000 ft and 12000 ft, varies linearly between ISA +10 oC and ISA +15oC i) At and above 12000 ft, ISA +15oC *The Equivalent Bare Engine Take -off Thrust quoted above is derived from the approved Net Take -off Thrust by excluding the losses attributable to the cold convergent -divergent nozzle, by-pass duct flow and leakage and the afterbody. I. MODELS RB211- Trent 892-17 RB211- Trent 884-17 RB211- Trent 884B-17 RB211- Trent 877-17 RB211- Trent 875-17 RB211- Trent 892B-17 RB211- Trent 895-17 PRINCIPAL DIMENSIONS, inches Length From front fan case flange to rear of tail bearing housing Radius, maximum 178 60 178 60 178 60 178 60 178 60 178 60 178 60 CENTER OF GRAVITY, inches Aft from powerplant station 100 Below centerline Starboard from engine centerline 27.4 1.8 0.1 27.4 1.8 0.1 27.4 1.8 0.1 27.4 1.8 0.1 27.4 1.8 0.1 27.4 1.8 0.1 27.4 1.8 0.1 WEIGHT Dry Basic Engine (lbs) 13400 13400 13400 13400 13400 13400 13400 ENGINE PARTICULARS BUILD STANDARD RR Drawing Introduction Sheet (DIS) 2184 Issue 2 2151 Issue 3 2219 Issue 1 2158 Issue 3 2157 Issue 3 2185 Issue 1 2175 Issue 1 FUELS APPROVED FUELS See relevant Engine Operating Instructions for approved fuels. APPROVED OILS See relevant Engine Operating Instructions for approved oils. OIL CAPACITY Nominal total system capacity Nominal oil tank capacity Minimum usable oil (including effect of attitude) 93.9 U.S. pints 49.2 U.S. pints 32.5 U.S. pints - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - TCDS E00050EN Page 3 of 7 LEGEND: “- -“ INDICATES “SAME AS PRECEDING MODEL” “- -“ INDICATES “NOT APPLICABLE” OIL CAPACITY (Cont) RB211- Trent 892-17 RB211- Trent 884-17 RB211- Trent 884B-17 RB211- Trent 877-17 RB211- Trent 875-17 RB211- Trent 892B-17 RB211- Trent 895-17 COMPONENTS ELECTRONIC FULL AUTHORITY FUEL CONTROL Fuel control, Lucas EEC Fuel pump, ArgoTech Fuel metering unit Lucas FMU 9000.07 721400-2 800MK3 9000.06AK1 - - - - 9000.7 - - - - - - - - - - - - - - - - 9000.07 - - - - - - 830800-1 800MK4 IGNITION SYSTEM Ignition system plugs Champion Ignition system units Simmonds CH34698 430081 - - - - - - - - - - - - - - - - - - - - CH34736 430154 EQUIPMENT For identification of equipment approved for use on these engines, refer to Rolls -Royce Report DNS12938. CERTIFICATION BASIS FAR 33 effective February 1, 1965, as amended by FAR 33-1 through 33-15. Pursuant to FAR 21.29(a)(1)(ii), the Type Certificate was issued in validation of the British Civil Aviation Authority Certification Standards JAR -E Change 8 plus OP E/91/1 which were found to provide a level of safety equivalent to tha t provided by FAR 33, Amendment 33 -15. APPLICATION ISSUED/ MODEL DATE REVISED DELETED RB211 TRENT 877-17 JUL 22, 1992 JAN 30, 1995 RB211 TRENT 884-17 JUL 22, 1992 JAN 30, 1995 RB211 TRENT 875-17 OCT 22, 1992 JAN 30, 1995 RB211 TRENT 890-17 JAN 19, 1994 JAN 30, 1995 FEB 28, 1997* RB211 TRENT 892-17 OCT 10, 1996 MAR 03, 1997 RB211 TRENT 892B-17 OCT 10, 1996 JUN 18, 1997 RB211 TRENT 895-17 OCT 06, 1998 JUL 16, 1999 RB211 TRENT 884B-17 AUG 13,1999 SEPT 16, 2003 *The Trent 890-17 engine was redesignated as the Trent 892-17 The aviation authority for the United Kingdom, the UK Civil Aviation Authority (CAA), originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E00050NE. Effective September 28, 2003, the E uropean Aviation Safety Agency (EASA) began oversight of this product on behalf of the UK. IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with UK CAA 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 E00050EN, 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." TCDS E00050EN Page 4 of 7 LEGEND: “- -“ INDICATES “SAME AS PRECEDING MODEL” “- -“ INDICATES “NOT APPLICABLE” NOTES NOTE 1. The engine ratings are based on static test stand operation under the following conditions: A. (1) Fan inlet air at 59oF and 29.92 in. Hg. (2) No aircraft accessory loads or optional bleed air extraction. (3) 100% intake recovery corrected from the datum air intake system defined by Drawings ATF14670 and ATF14542 or approved alternatives. (4) Engine exhaust system defined by Primary Nozzle to 314W5510/1, Tail Plug to 314W5520/1, slave C-Ducts to RX75502. (5) Turbine gas temperature and rotor speed limitations are not exceeded. NOTE 2. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS (%) 100% HP = 10,611 rpm / 100% IP = 7,000 rpm / 100% LP = 3,300 rpm. Takeoff (5 minutes, see NOTE 19) HP Pre-mod 72-B672 100.5 Post-mod 72-B672 102.5 IP 105.0 LP 100.5 Maximum reverse thrust (33 seconds) LP 80.5 Maximum overspeed (20 second limit) HP IP LP Pre-mod 72-B672 100.9 107 101.2 Post-mod 72-B672 102.8 107 101.2 NOTE 3. MAXIMUM PERMISSIBLE TEMPERATURES TURBINE GAS TEMPERATURE (Indicated) (TGT) oC Starting 700 Momentary maximum during start or relight Takeoff (5 minutes, see NOTE 19) 900 Maximum continuous (unrestricted) 850 Overtemperature (20 seconds) 920 FUEL At outlet from HP fuel pump Unrestricted 140oC Max. during transient overshoots on reducing rpm (15 min. limit) 165oC OIL Combined scavenge Minimum for starting -40oC Minimum for opening up 50oC Maximum for unrestricted use 191oC NOTE 4. FUEL AND OIL PRESSURE LIMITS FUEL Maximum pressure at the engine inlet (measured at inlet of LP fuel pump) Continuous 60 psig (414 kPa) Transient 70 psig (483 kPa) Static 170 psig (1,172 kPa) TCDS E00050EN Page 5 of 7 LEGEND: “- -“ INDICATES “SAME AS PRECEDING MODEL” “- -“ INDICATES “NOT APPLICABLE” NOTE 4 (Cont.) FUEL (continued) MINIMUM FUEL PRESSURE Between sea level and 45,000 feet, not less than 5 psig plus true fuel vapor pressure, measured at inlet to engine LP fuel pump. Operation with aircraft boost pumps inoperative, kerosene fuel types only: For engine operation with the aircraft boost pumps inoperative the engine minimum fuel pre ssure limit is reduced down to 1.1 psi (7.6 kPa) at altitudes of up to 43,100 ft (13,140 m) for up to 750 minutes. Refer to the Installation Manual for additional information. OIL Measured between oil pump and internal gearbox scavenge oil return line. Minimum acceptance for flight Ground idle to 70% HP rpm 35 psid At and above 95% HP rpm 60 psid Minimum to complete flight Ground idle to 70% HP rpm 25 psid At and above 95% HP rpm 50 psid NOTE 5. MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS Air delivery for aircraft services, excluding powerplant anti -icing. This air is automatically scheduled from the engine IP stage 8 and HP stage 6 compressor bleed ports via two valves in the ai rcraft ducting which select the appropriate supply in response to signals sensing the HP compressor delivery pressure (P30), IP delivery pressure (P25), altitude and corrected HP compressor speed. The switchover from the HP to the IP compressor delivery bleed po rt occurs whenever the following conditions are met: 1. P25 at the IPS check value is greater than 44 psig + 5 up to 22,000 feet. 2. Above 22,000 feet there are two bleed switchover levels, both varying as a function of altitude and corrected HP compressor speed. The upper and lower switch points vary linearly from 37.7 and 32.5 psig at 30,000 feet to 32.5 and 21 psig at 43,000 feet. Otherwise bleed air is extracted from the HP bleed port. Maximum HP6 bleed (% gas generator compressor flow); This bleed decreases linearly between the values listed below for the 957 oC turbine entry temperature (TET) (1192 oC abnormal operation) and switchover points 1. Normal Operation i. Low idle and up to 957 oC TET ii At switchover point 2. Abnormal (One engine operation) i. Low idle and up to 1192 oC TET ii. At switchover point Maximum IP8 bleed (% gas generator compressor flow); This bleed (IP8) decreases linearly between the values listed below for the maximum continuous and maximum takeoff points 1. Normal Operation i. At switchover and up to max. cont. ii. At maximum takeoff 2. Abnormal (one engine operation) i. At switchover and up to max. cont. ii. At maximum takeoff Maximum LP bleed (%) of fan flow) Normal & Abnormal (one engine operation) Air delivery for powerplant anti -icing Maximum HP3 bleed (%HPC inlet flow) This bleed decreases linearly between the values listed below for the 777 oC TET and takeoff points I. At low idle and up to 777 oC ii. At takeoff 11.5% 5.4% 11.5% 7.3% 5.0% 2.2% 6.0% 3.4% 0.8% 0.63% 0.57% TCDS E00050EN Page 6 of 7 LEGEND: “- -“ INDICATES “SAME AS PRECEDING MODEL” “- -“ INDICATES “NOT APPLICABLE” NOTE 6. SHAFT POWER EXTRACTION LIMITATIONS Accessory drive provisions (continuous power as listed may be extracted under all engine operating conditions) MODELS DRIVE ROTATION SPEED RATIO TO HP ROTOR SPEED TORQUE (pound - inches) OVERHANG (in.-lbs) CONTINUOUS MAXIMUM INSTANTANEOUS ALL MODELS STARTER IDG HYDRAULIC PUMP VSCF CCW CCW CCW CCW 0.9998 N3 0.8544 N3 0.3916 N3 2.3495 N3 SEE 2956 1500 240 BELOW 5000 1730 400 290 1165 250 400 CW = CLOCKWISE CCW = COUNTERCLOCKWISE Max Starter torque varies with air temperature as follows: - Air temperature oC Max torque (lbs - in) 10 -20 -40 7440 8640 10800 NOTE 7. Power setting, power check, and control of the engine output are based on engine pressure ratio (EPR) targets calculated by the EEC. Pressure probes are included in the engine for measurement of EPR. NOTE 8. Life-limited parts are identified in Time Limits Manual (See NOTE 10). NOTE 9. This engine approval includes bare engine plus engine mounting feet, core engine cowlings, and engine accessories, coolers, filters, harness , and instrumentation transmitters as defined in the appropriate RR DIS. Hydraulic pump, VSCF and IDG are aircraft supply. NOTE 10. RB211 series manuals under JAA requirements accepted as equivalent to FAR 33.4 and 33.5 requirements are: RB211-TRENT 800 SERIES OPERATING INSTRUCTIONS MAINTENANCE MANUAL INSTALLATION MANUAL ENGINE MANUAL TIME LIMITS MANUAL ALL MODELS F-TRENT-777 D633W101-RRY EL 2839 E-TRENT-2RR T-TRENT-2RR 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 United Kingdom Civil Aviation Authority. 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. • Technical Variances These approvals pertain to the type design only. NOTE 11. These engines meet the smoke and gaseous emission requirements of FAR 34. NOTE 12. These engines are fitted with a Digital Electronic Engine Fuel Control system in which the software meets the "critical" standard of RTCA DO-178A/ED12A. NOTE 13. In icing conditions, the engine may be operated satisfact orily at LP rotor speeds (N1) down to low idle. Minimum corresponding N1 at low idle for these engines is 20.9 percent airborne and 18 percent on the ground. NOTE 14. These engines are fitted with an independent LP spool overspeed governor. Dispatch with this item unserviceable is not permitted. TCDS E00050EN Page 7 of 7 LEGEND: “- -“ INDICATES “SAME AS PRECEDING MODEL” “- -“ INDICATES “NOT APPLICABLE” NOTE 15. These engines satisfy the certification basis as defined in this Data Sheet when operating with the EEC in reversionary control mode. NOTE 16. VARIANTS RB211-Trent 892-17 Basic model. RB211-Trent 884-17 Same as basic model except for decreased thrust ratings. RB211-Trent 877-17 Same as basic model except for decreased thrust ratings. RB211-Trent 875-17 Same as basic model except for decreased thrust ratings. RB211-Trent 892B-17 Same as basic model except for increased takeoff thrust rating at altitudes between 2,000 feet and 8,000 feet. RB211-Trent 895-17 Same as basic model but with increased takeoff thrust rating. RB211 Trent 884B-17 Same as basic model except for decr eased thrust ratings. NOTE 17. The RB211 Trent 800 series engines have been approved to operate with certain faults present in the control system, based on satisfaction of FAR 33 requirements and appropriate FAR 25 control system reliability requirements. Criteria pertaining to the dispatch and maintenance requirements for the engine control system are specified in Rolls-Royce plc report DNS 14049. The airframe manufacturers may use different nomenclature in adapting these fault categories to the aircraft maintenance and display systems; however, the maximum operating intervals are restricted as shown above. NOTE 18. These engines are approved for use with Boeing Thrust Reverser Part Number 315W5000 -1/-2. NOTE 19. The take-off rating and its associated operating limitations may be used for up to 10 minutes in the event of engine out contingency, but their use is otherwise limited to not more than 5 minutes. ----END----