# TCDS E00075EN: Rolls-Royce Deutschland Ltd & Co KG - Type: Type certificate data sheet - Status: Current - Holder: Rolls-Royce Deutschland Ltd & Co KG - Revision: 2 - Revised: June 30, 2026 - Product: Engine - Certification basis: Part 33 - Data sheet PDF: https://openairdocs.org/files/sha256/e2/00/e2000d951f19e00cb955e78611ef5669b73f400c5781083d9bfeb228b742b4b7 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID126476330520260710153107.0001 - Page: https://openairdocs.org/tcds/E00075EN ## Models (2) As the data sheet lists them. - RB211-TRENT 970-84 - RB211-TRENT 972-84 ## 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 REV. 2 2 2 PAGE 8 REV 2 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN . U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00075EN TCDS NUMBER E00075EN DATE: June 30, 2026 Revision 2 ROLLS-ROYCE, Deutschland Ltd. & Co. KG MODELS: RB211-TRENT 970-84 RB211-TRENT 972-84 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00075EN) 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 Eschenweg 11, 15827 Blankenfelde-Mahlow, Germany TYPE CERTIFICATE (TC) RECORD: Rolls-R oyce, plc transferred TC E00075EN to Rolls-Royce, Deutschland on February 21, 2019 I. MODELS RB211-Trent 970-84 RB211-Trent 972-84 TYPE High by-pass turbofan axial flow, three- rotor. Single-stage low pressure fan with a swept fan blade (9.68 ft diameter) and OGVs to increase efficiency and reduce noise 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. The LP and IP assemblies rotate independently in a counter-clockwise direction. The HP assembly rotates clockwise aft looking fwd (ALF). The engine control system utilizes an Electric Engine Control (EEC) which has an airframe interface for digital bus communications (AFDX). RATINGS (See NOTE 1) Maximum continuous Thrust, pounds net at sea level static Takeoff (5 minutes, see NOTE 20) Thrust, pounds net at sea level static Equivalent bare engine thrust, pounds (see NOTE 9) 71,850 75,152 76,155 -- 76, 752 77,766 TCDS E00075EN Page 2 of 8 1. The 970-84 and 972-84 are flat rated to ISA + 15oC at all altitudes I. MODELS RB211- Trent 970-84 RB211- Trent 972-84 PRINCIPAL DIMENSIONS, inches Length From tip of spinner minus rubber tip to Tail Bearing Housing Radius, around center- line includes VFG cooler, not including drains mast 209 77.5 - - - - CENTER OF GRAVITY, inches Aft from powerplant station 100 Below centerline Starboard from engine centerline 23.1 0.6 -2.8 - - - - - - WEIGHT Dry Basic Engine (lbs) (not including fluids and Nacelle EBU) 13842 - - ENGINE PARTICULARS BUILD STANDARD RR Drawing Introduction Sheet (DIS) 2244 Issue 3 2274 - - 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) 35.5 22.2 12 - - - - - - TCDS E00075EN Page 3 of 8 RB211- Trent 970-84 RB211- Trent 972-84 COMPONENTS ELECTRONIC FULL AUTHORITY DIGITAL ENGINE CONTROL (FADEC) Hamilton Sunstrand EEC Software standard Engine Monitorng Unit Vibrometer Software standard 1002600-1 RRA380-402 271-123-034-034 271-123-811-201 - - - - - - - - IGNITION SYSTEM Ignition system plugs Goodrich Rosemount (Champion) Ignition system units Goodrich Rosemount (Champion) CH34829 CH92077 - - - - EQUIPMENT For identification of equipment approved for use on these engines, refer to Rolls-Royce installation manual DKC 237292. CERTIFICATION BASIS FAR 33 effective February 1, 1965, as amended by FAR 33-1 through 33-20. Pursuant to FAR 21.29(a)(1)(ii), the Type Certificate was issued in validation of the Joint Aviation Authorities Certification Standards JAR-E Change 11 dated 1 November 2001, and EASA CS-E 800(c) issue 1 for large flocking bird ingestion which were found to provide a level of safety equivalent to that provided by FAR 33.76. The FAA validated this product under U.S. Type Certificate Number E00075EN. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the UK. MODEL APPLICATION DATE ISSUED DATE RB211 TRENT 970-84 October 1, 2002 December 4, 2006 RB211 TRENT 972-84 April 11, 2005 December 4, 2006 RB211 TRENT 970B-84 October 1, 2002 December 4, 2006 (Deleted June 30, 2026) RB211 TRENT 977-84 October 1, 2002 December 4, 2006 (Deleted June 30, 2026) RB211 TRENT 980-84 October 1, 2002 December 4, 2006 (Deleted June 30, 2026) RB211 TRENT 977B-84 May 6, 2003 December 4, 2006 (Deleted June 30, 2026) RB211 TRENT 972B-84 April 11, 2005 December 4, 2006 (Deleted June 30, 2026) TCDS E00075EN Page 4 of 8 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 EA SA 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 E00075EN, is in a condition for safe operation and has undergone a final operational check. Reference FAR Section 21.500, which provides for the airworthiness acceptance of aircraft engines manufactured outside of the United States for which a U.S. 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 E00075EN Page 5 of 8 NOTES NOTE 1. The engine thrust rating is for an engine on a test bed running at the same TET as an engine installed on an aircraft, operating to a rated thrust at kink point day temperature, at the point of rotation for take-off. The bare engine thrust is the take-off thrust plus the thrust that is lost through engine nacelle, by-pass duct and nozzle leakages and inefficiencies, recognizing that these components do not form part of the engine type design. NOTE 2. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS (%) 100% HP = 12,200 rpm / 100% IP = 8,300 rpm / 100% LP = 2,900 rpm. Takeoff (5 minutes, see NOTE 20) HP 97.8% IP 97.8% LP 96.1% Maximum continuous (see note 22) HP 97.7% IP 97.8% LP 96.1% NOTE: Stabilized operation in the speed range 64% to 72% NL or above 78% NL is not permitted during static operations with forward airspeed less than 45 knots. Passing through the speed range of 64% to 72% while increasing or decreasing thrust is permitted. NOTE 3. MAXIMUM PERMISSIBLE TEMPERATURES TURBINE GAS TEMPERATURE (TGT) - Trimmed (oC): Starting (Momentary maximum during starts below 50% HP speed): 700 Maximum for Takeoff (5 minutes) (see NOTE 20) 900 Maximum continuous (unrestricted) 850 Maximum Overtemperature (20 seconds) 920 (See NOTE 21) Maximum during relights in flight 850 NOTE: TGT is measured by thermocouples positioned at the 1st stage Nozzle Guide Vane of the LP Turbine. FUEL (°C): (See NOTE 15) Minimum fuel temp in flight: -54 (or the freeze point, whichever is higher Minimum fuel temp for ground starting: -20 (for the Hydro Mechanical Unit and LP fuel filter) Maximum fuel temp (i) On ground to top of climb: 55 (ii) At top of descent: 50 OIL (°C) Combined scavenge Minimum for starting -10 Minimum for opening up 60 Maximum for unrestricted use 196 NOTE 4. PRESSURE LIMITS: FUEL Pressure (psi): Minimum Fuel Pressure (psi) Minimum absolute inlet pressure (measured at the pylon interface): 5 TCDS E00075EN Page 6 of 8 NOTE 4 (Cont.) FUEL pressure:(continued): Maximum pressure at the engine inlet (measured at the pylon interface) (i) Continuous 40 (ii) Transient 100 (iii) Static 50 OIL pressure (psi): Minimum Oil pressure (psi): (i) Ground idle to 70% HP rpm 25 (ii) Above 95% HP rpm 50 Maximum Allowable Oil Consumption (l/hr): 0.46 NOTE 5. MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS The maximum allowable air delivery for aircraft services, excluding powerplant anti-icing is given below. This air is automatically scheduled from the engine IP stage 8 at take-off, cruise and climb and HP stage 6 compressor bleed ports at descent and idle ground conditions. At holding conditions (from 5,000 ft to 30,000 ft), switchover from IP8 to HP6 Stage bleed occurs.  At normal operating conditions (4 bleeds and 2 aircraft air-conditioning packs), air is bled from the IP off-take whenever IP port pressure is greater than 30.0 psi. For IP off-take pressures lower than this value, air is bled from the HP off-take.  At abnormal operating conditions (2 bleeds and 1 aircraft air-conditioning pack), air is bled from the IP off-take as long as the IP port pressure is greater than 33.5 psi (34.5 psi in icing conditions); otherwise, air is bled from the HP off-take. Maximum HP6 bleed (% W26): This bleed decreases linearly between the values listed below for the 1020oC turbine entry temperature (TET) and switchover points. 1. Normal Operation i. Low idle and up to 1020 oC TET ii 1020 oC to 1218 oC 2. Abnormal (One engine operation) i. Low idle and up to 1103 oC TET ii. 1103 oC to 1173 oC ii. 1173 oC to 1258 oC Maximum IP8 bleed (% W24): This bleed (IP8) decreases linearly between the values listed below for the maximum continuous and maximum takeoff points. 1. Normal Operation i. 1218 oC to 1393 oC ii. 1393 oC to 1488 oC iii. 1488 oC to Max take-off 2. Abnormal (One engine operation) i. 1258 oC to 1504 oC ii. 1504 oC to Max take-off AIR DELIVERY FOR POWERPLANT ANTI-ICING Maximum HP3 bleed (%W26): This bleed decreases linearly between the values listed below The nacelle thermal anti-icing flow demand (HP3) is modulated via a regulating valve to provide a constant flow function at the engine/ nacelle. 1. Normal Operation i. Low idle to 888oC ii. 888 oC to 1293 oC iii. 1293 oC to 1548 oC iv. 1548 oC to Max take-off 2. Abnormal (One engine operation) i. Low idle to 888 oC ii. . 888 oC to 1293 oC iii. 1293 oC to 1548 oC iv. 1548 oC to Max take-off 12.1 to 11.8 11.8 to 5.3 13.5 to 13.1 13.1 to 13.1 13.1 to 13.1 5.9 to 3.8 3.8 to 1.7 1.7 to 1.8 6.3 to 3.3 3.3 to 3.1 1.6 to 1.5 1.5 to 1.4 1.4 to 1.2 1.2 to 1.1 1.8 to 1.8 1.8 to 1.3 1.3 to 0.8 0.8 to 0.8 TCDS E00075EN Page 7 of 8 Precooler flow (%W120) varies linearly between the points listed. 1. Normal and Abnormal Operation i. Idle to 1101 oC ii 1101 oC to 1328 oC iii. 1328 oC to 1598 oC 0.62 0.62 to 0.27 0.27 NOTE 6. SHAFT POWER EXTRACTION LIMITATIONS Accessory drive provisions (continuous power as listed may be extracted under all engine operating conditions) TORQUE (pound - inches) MODELS DRIVE ROTATION SPEED RATIO TO HP ROTOR SPEED CONTINUOUS MAXIMUM INSTANTANEOUS OVERHANG (in.-lbs) ALL MODELS HYDRAULIC PUMPs VFG CCW CCW 0.33 1.81 8497 8860 403 1172 CW = CLOCKWISE CCW = COUNTERCLOCKWISE NOTE 7. Reserved NOTE 8. Life-limited parts are identified in Time Limits Manual (See NOTE 10). NOTE 9. The Equivalent Bare Engine Take-off and Maximum Continuous thrust quoted above are derived from the approved Net Take-off and Net Maximum Continuous thrust by excluding the losses attributable to the inlet, cold convergent nozzle, hot nozzle, by-pass duct flow leakage and the after body. No bleed or power off takes are assumed. NOTE 10. RB211 series manuals under EASA requirements accepted as equivalent to FAR 33.4 and 33.5 requirements are: RB211-TRENT 900 SERIES OPERATING INSTRUCTIONS MAINTENANCE MANUAL INSTALLATION MANUAL ENGINE MANUAL TIME LIMITS MANUAL ALL MODELS OI-Trent-A380 M-Trent-A380 DKC-237292 E-Trent-A380 T-Trent-9RR Each of the documents listed above must state that it is approved by the European Aviation Safety Agency (EASA). 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. The software of the Engine Electronic Control is designated Level “A” as defined by RTCA DO-178B/ED12B. NOTE 13. The software of the Engine Monitoring Unit is designated Level “C” as defined by RTCA DO-178B/ED12B. NOTE 14. EMI/ Lightning (Refer to the Installation Manual for details.) TCDS E00075EN Page 8 of 8 NOTE 15. The fuel temperature is taken as that in the wing tank. The minimum and maximum fuel temperature and pressure are not measured on the engine and therefore, not provided to the flight deck. However, the wing tank temperature is available on the flight deck and is assumed that there is negligible difference in temperature between the tank and the engine inlet. NOTE 16. The acceleration from 15% to 95% of the Trent 980 rated take-off power is 5.6 seconds. NOTE 17. VARIANTS RB211-Trent 970-84 Basic model. RB211 Trent 972-84 Same as basic model except for increased thrust ratings NOTE 18. The engine models (RB211 Trent 970-84 and 972-84,) have not been approved for Time Limited Dispatch. NOTE 19. These engines are approved for use with Aircelle Thrust Reverser Unit (TRU) at the inboard engine positions (Part number ASE 0010-XX-0 for the left hand installation and ASE 0050-XX-0 for the right hand installation) and for a fixed fan duct (FFD) in the outboard engine positions (Part numbers ASE 5010-XX-0 for the left hand installation and ASE 5050-XX-0 for the right hand installation), The TRU and FFD do not form part of the engine type design and must be certified as part of the aircraft type design. NOTE 20. 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. NOTE 21. The engine models (RB211 Trent 970-84 and , 972-84,) are approved for a maximum exhaust gas overtemperature of 920°C for inadvertent use for periods of up to 20 seconds without requiring maintenance action. The cause of the overtemperature must be investigated and corrected. NOTE 22. No overhaul is authorized until the EM and MM are approved and delivered. NOTE 23 The maximum Continuous Speed limitations defined in this Data Sheet are not displayed as limitations on the A380 flight deck. In accordance with the equivalent safety finding against JAR-E740(f), non display of these limitations is acceptable. NOTE 24 On February 5, 2026, EASA notified the FAA of Rolls-Royce, Deutschland Ltd. & Co. KG’s request to surrender the TC for engine models RB 211 Trent 970B-84, Trent 972B-84, Trent 977-84, Trent 977B-84 and Trent 980-84. The FAA has concurred with Rolls-Royce’s request to surrender the TC for the aforementioned engine model. The FAA has revised E00075EN accordingly to remove mention of those engine models. Import of these engine models into the US is prohibited. -END- ``` ## ADs (17, in force first) - [AD 2025-05-04](https://openairdocs.org/ad/2025-05-04): Engine Drains · Rolls-Royce Deutschland RB211-TRENT 970-84 and RB211-TRENT 972-84. Effective Apr 1, 2025 - [AD 2018-18-06](https://openairdocs.org/ad/2018-18-06): Turbine Section · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective Sep 20, 2018 - [AD 2017-08-10](https://openairdocs.org/ad/2017-08-10): Engine · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective May 9, 2017 - [AD 2015-02-20](https://openairdocs.org/ad/2015-02-20): Intermediate-pressure compressor (IPC) rotor shaft · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 22 more. Effective Mar 11, 2015 - [AD 2013-05-04](https://openairdocs.org/ad/2013-05-04): Piston ring · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective Apr 30, 2013 - [AD 2013-02-03](https://openairdocs.org/ad/2013-02-03): Fuel oil heat exchanger (FOHE) · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective Jan 24, 2013 - [AD 2012-24-05](https://openairdocs.org/ad/2012-24-05): Oil transfer tube · Rolls-Royce RB211-TRENT 970-84 and RB211-TRENT 972-84. Effective Dec 26, 2012 - [AD 2012-12-03](https://openairdocs.org/ad/2012-12-03): IP turbine · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective Jul 17, 2012 - [AD 2011-06-11](https://openairdocs.org/ad/2011-06-11): Pressure turbine · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective Apr 4, 2011 - [AD 2009-18-13](https://openairdocs.org/ad/2009-18-13): HP Turbine Nozzle Guide Vane (NGV) Convex Surfaces · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective Oct 14, 2009 - [AD 2019-05-02](https://openairdocs.org/ad/2019-05-02) (historical): Powerplant/Engine Drains · Rolls-Royce RB211-TRENT 970-84 and RB211-TRENT 972-84. Effective Mar 27, 2019 - [AD 2017-22-13](https://openairdocs.org/ad/2017-22-13) (historical): Powerplant/Engine Drains · Rolls-Royce RB211-TRENT 970-84 and RB211-TRENT 972-84. Effective Nov 22, 2017 - [AD 2017-01-01](https://openairdocs.org/ad/2017-01-01) (historical): Engine (Turbine/Turboprop) · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective Jan 26, 2017 - [AD 2014-05-25](https://openairdocs.org/ad/2014-05-25) (historical): Low-pressure turbine exhaust case and support assembly or tail bearing housing · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective Apr 7, 2014 - [AD 2013-15-10](https://openairdocs.org/ad/2013-15-10) (historical): Cracking on the IP compressor rotor shaft rear balance land · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 22 more. Effective Oct 8, 2013 - [AD 2013-02-04](https://openairdocs.org/ad/2013-02-04) (historical): Low-pressure turbine (LPT) stage 2 disk interstage seal material loss and increased low-pressure rotor vibration while in flight · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective Feb 14, 2013 - [AD 2010-16-07](https://openairdocs.org/ad/2010-16-07) (historical): IP turbine · Rolls-Royce RB211-TRENT 970-84, RB211-TRENT 970B-84, RB211-TRENT 972-84 and 4 more. Effective Sep 17, 2010 --- 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.