TCDS E00086EN

LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES “NOT APPLICABLE" PAGE 1 2 3 4 5 6 7 8 9 REV. 9 8 9 8 7 8 7 8 8 PAGE 10 11 12 13 14 REV. 9 8 9 7 7 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00086EN TCDS NUMBER E00086EN DATE: 30-June-2026 Revision 9 ROLLS-ROYCE, Deutschland Ltd. & Co. KG MODELS: Trent XWB-75 Trent XWB-79 Trent XWB-79B Trent XWB-84 Trent XWB-97 Trent XWB-79EP Trent XWB-75EP Trent XWB-79BEP Trent XWB-84EP Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00086EN) 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-Royce, plc transferred TC E00086EN to Rolls-Royce Deutschland on February 21, 2019 TYPE The engine is a three shaft high bypass ratio, axial flow, turbofan with low pressure, intermediate pressure and high pressure compressors driven by separate turbines through coaxial shafts. The LP compressor fan diameter is 118 inches with a swept fan blade and outlet guide vanes. The combustion system consists of a single annular combustor with 20 fuel spray nozzles. The LP and IP assemblies rotate independently in a counter clockwise direction; the HP assembly rotates clockwise, when viewed from back of the engine looking forward. The compressor and turbine have the following features: Compressor Turbine LP - single stage LP - 6 stage IP - 8 stage IP - 2 stage HP - 6 stage HP - single stage The engine control system utilizes an electronic engine controller (EEC) which has an airframe interface for digital bus communications. An engine monitoring unit (EMU) is fitted to provide vibration signals to the aircraft. TCDS E00086EN Page 2 of 14 I. MODELS Trent XWB-75 Trent XWB-79 Trent XWB-79B Trent XWB-84 Trent XWB-97 RATINGS (See NOTE 1) Takeoff (5 min) Thrust, (net) - lbf (See NOTE 13) 74,200 78,900 - - 84,200 97,000 Maximum continuous Thrust, (net) - lbf 66,600 71,400 - - - - 83,100 PRINCIPAL DIMENSIONS, inches Length – from front edge of A1 flange – fan case – to rear edge of A7 flange – tail bearing housing 176.5 - - - - - - - - Radius – from centerline not including drain mast 78.8 - - - - - - - - CENTER OF GRAVITY, Wet, inches Offset from the center of front engine mount (power plant station 3000mm) 34.4 - - - - - - 34.0 Offset from Horizontal Centerline -1.0 - - - - - - -1.2 Offset from Vertical Centerline 1.1 - - - - - - 1.2 WEIGHT Maximum dry engine weight without fluids, nacelle and aircraft interface parts (lbs) 16,043 - - - - - - 16,643 ENGINE BUILD STANDARD Rolls-Royce Drawing Introduction Sheet (DIS) DIS 2304 Issue 3 DIS 2338 Issue 3 DIS 2339 Issue 3 DIS 2306 Issue 3 DIS2341 Issue 3 + MB72-K939 TCDS E00086EN Page 3 of 14 II. MODELS Trent XWB-75EP Trent XWB-79EP Trent XWB-79BEP Trent XWB-84EP RATINGS (See NOTE 1) Takeoff (5 min) Thrust, (net) - lbf (See NOTE 13) Maximum continuous Thrust, (net) - lbf 74,200 66,600 78,900 71,400 - - - - 84,200 - - PRINCIPAL DIMENSIONS, inches Length – from front edge of A1 flange – fan case – to rear edge of A7 flange – tail bearing housing Radius – from centerline not including drain mast 176.5 78.8 - - - - - - - - - - - - CENTER OF GRAVITY, Wet, inches Offset from the center of front engine mount (power plant station 3000mm) Offset from Horizontal Centerline Offset from Vertical Centerline 34.9 -1.1 1.1 - - - - - - - - - - - - - - - - - - WEIGHT Maximum dry engine weight without fluids, nacelle and aircraft interface parts (lbs) 15,432 - - - - - - ENGINE BUILD STANDARD Rolls-Royce Drawing Introduction Sheet (DIS) DIS 2392 Issue 3 DIS 2393 Issue 3 DIS 2394 Issue 3 DIS 2395 Issue 3 APPROVED FUELS See Civil Engines - Engine Fuels Manual - Publication reference PMC- ROLLSROYCEFUEL-K0680 EFMC0-01 for approved fuels and additives. APPROVED OILS See Civil Large Engines - Engine Oils Manual – Publication reference EOM-CIVIL-1RR. OIL CONSUMPTION Oil consumption limits apply to the actual approved diversion time as specified in the A350 ETOPS CMP. TCDS E00086EN Page 4 of 14 EQUIPMENT For details of equipment included in the type design definition refer to the Installation manual. For details of equipment supplied by the Airframe TC holder, refer to the installation manual. A thrust reverser unit is not part of the engine type design and is certified as part of the aircraft type design. The engine is approved for operation with a thrust reverser unit. CERTIFICATION BASIS Trent XWB-75, -79, -79B and -84 Trent XWB-97 Trent XWB-75EP, -79EP, - 79BEP, -84EP Airworthiness Standards: 14 CFR part 33, effective February 1, 1965, including Amendments 33-1 through 33-31 inclusive, with an exemption to § 33.27(f)(6), No. 15079 dated February 29, 2016. Environmental Standards: 14 CFR part 34, Amendment 7A, effective May 24, 2024. See NOTE 11 for a detailed summary of the certification basis for fuel venting and exhaust emissions. 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 TC3013EN-E-P-9) Pursuant to 14 CFR 21.29(a)(1)(ii), the Type Certificate was issued in validation of the European Aviation Safety Agency (EASA) Certification Standards CS-E, amendment 2 effective December 18, 2009, CS-E 1030 amendment 3, and CS-E 1040 amendment 3, which were found to provide a level of safety equivalent to that provided by 14 CFR part 33 effective February 1, 1965, as amended by 33-1 through 33-31. Airworthiness Standards: 14 CFR part 33 effective February 1, 1965, as amended by 33-1 through 33-33 inclusive, with an exemption to § 33.27(f)(6), No. 17441 dated August 16, 2017. Environmental Standards: 14 CFR part 34, Amendment 7A, effective May 24, 2024. See NOTE 11 for a detailed summary of the certification basis for fuel venting and exhaust emissions. 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 TC3013EN-E-P-9) • § 33.27(b)(3) Rotor Overspeed, IPTOS/LPTOS Deactivation (documented in ELoS memo AT03491EN-E-P-13) • § 33.27(d) Rotor Overspeed, Rotor Growth Assessment (documented in ELoS memo AT03561EN-E-P-19) • § 33.83(a), (b), and (c) Vibration Test (documented in ELoS memo AT03491EN-E-P-2) Pursuant to 14 CFR 21.29(a)(1)(ii), the Type Certificate was issued in validation of the European Aviation Safety Agency (EASA) Certification Standards CS-E, amendment 3 dated December 23, 2010, and CS-E 650 amendment 4, which were found to provide a level of safety equivalent to that provided by 14 CFR Part 33 effective February 1, 1965, as amended by 33-1 through 33-33. Airworthiness Standards: 14 CFR part 33 effective February 1, 1965, as amended by 33-1 through 33- 31 inclusive, with exemptions to §33.27(c), No. 22976 dated October 9, 2024, and §33.27(f)(6), No. 22975 dated October 9, 2024. Environmental Standards: 14 CFR part 34, Amendment 7A, effective May 24, 2024. See NOTE 11 for a detailed summary of the certification basis for fuel venting and exhaust emissions. An Equivalent Level of Safety Finding has been made for the following regulations. • 14 CFR 33.78(a)(1) Large Hailstone Ingestion (documented in ELoS memo TC3013EN-E-P-9) • §33.27(b)(3) Rotor Overspeed, IPTOS/LPTOS Deactivation (documented in ELoS memo AT03491EN-E-P-13) • §33.27(d) Rotor Overspeed, Rotor Growth Assessment (documented in ELoS memo AT03561EN-E-P-19) • §33.83(a), (b), and (c) Vibration Test (documented in ELoS memo AT03491EN-E-P-2) Pursuant to 14 CFR 21.29(a)(1)(ii), the Type Certificate was issued in validation of the European Aviation Safety Agency (EASA) Certification Standards CS-E, amendment 4 dated March 12, 2015. TCDS E00086EN Page 5 of 14 APPLICATION MODEL DATE ISSUED DELETED Trent XWB-75 May 14, 2009 October 3, 2013 Trent XWB-79 May 14, 2009 October 3, 2013 Trent XWB-79B May 14, 2009 October 3, 2013 Trent XWB-84 May 14, 2009 October 3, 2013 Trent XWB-97 July 14, 2014 November 20, 2017 Trent XWB-75EP October 16, 2019 February 13, 2025 Trent XWB-79EP October 16, 2019 February 13, 2025 Trent XWB-79BEP October 16, 2019 February 13, 2025 Trent XWB-84EP October 16, 2019 February 13, 2025 NOTES NOTE 1. ENGINE RATINGS: The engine ratings are based on sea-level static, International Standard Atmosphere (ISA) conditions. No power take-offs are assumed. All models are flat rated to ISA + 15ºC except the Trent XWB-79B, which is flat rated to ISA+21.6ºC. NOTE 2. TEMPERATURE LIMITS: TURBINE GAS TEMPERATURE (TGT) Trimmed/indicated °C Measured at the 1st stage Nozzle Guide Vane of the LP Turbine. Trent XWB-75, -75EP, -79, -79EP, -79B, -79BEP, -84, and -84EP Maximum Ground Starting and Shutdown 700 Maximum Inflight Relights 900 Maximum Takeoff (5 min., see NOTE 13) 900 Maximum Continuous (unrestricted duration) 850 Maximum Exhaust Gas Overtemperature (see NOTE 13) 920 Trent XWB-97 Maximum Ground Starting and Shutdown 700 Maximum Inflight Relights 900 Maximum Takeoff (5 min., see NOTE 13.) 900 Maximum Takeoff (2 min. out of a total of 5 minutes, see NOTE 13) 900 Maximum Continuous (unrestricted duration) 850 Maximum Exhaust Gas Overtemperature (see NOTE 13) 920 FUEL oC Measured at the pylon inlet to the engine. Trent XWB-75, -75EP, -79, -79EP, -79B, -79BEP, -84, -84EP and -97 Minimum Fuel Temperature (ground starts) -54 (or fuel freezing point, whichever is higher) Minimum Fuel Temperature (in flight) -54 (or fuel freezing point, whichever is higher) Maximum Fuel Temperature 55 Refer to the engine Installation Manual for additional information. OIL oC Measured at the oil tank outlet. Trent XWB-75, -79, -79B and -84 Minimum for starting -40 Minimum for acceleration to power, 50 Maximum for unrestricted use 180 TCDS E00086EN Page 6 of 14 NOTE 2. continued Trent XWB-75EP, -79EP, -79BEP and -84EP Minimum for starting -40 Minimum for acceleration to power 50 Maximum for unrestricted use 188 Trent XWB-97 Minimum for starting -40 Minimum for acceleration to power, 50 Maximum for unrestricted use 185.7 (Pre SB 73-K304) 188.1 (Post SB 73-K304) NOTE 3. PRESSURE LIMITS: FUEL Trent XWB-75, -75EP, -79, -79EP, -79B, -79BEP, -84 and -84EP Minimum absolute pressure at engine inlet 5 psi + Fuel True Vapor Pressure Maximum absolute pressure at the pylon interface: Steady state conditions with engine running 70 psi Transient conditions with engine running (2 seconds) 185 psi Static after engine shutdown 100 psi Trent XWB-97 Minimum absolute pressure at engine inlet 5 psi + Fuel True Vapor Pressure Minimum absolute pressure increases with reducing altitude below 14,600 feet Maximum absolute pressure at the pylon interface: Steady state conditions with engine running 70 psi Transient conditions with engine running (2 seconds) 185 psi Static after engine shutdown 100 psi OIL Trent XWB-75, -79, -79B and -84 without Service Bulletin 73-J148 or Modification 73-J148 Incorporated Minimum Ground idle to 70% HP rotor rpm 25 psi Minimum between 70% and 92.5% HP rpm increasing linearly from 25 psi to 48 psi Minimum between 92.5% and 96.0% HP rpm increasing linearly from 48 psi to 75 psi Minimum between 96.0% and 97.0% HP rpm 75 psi Minimum between 97.0% and 97.5% HP rpm increasing linearly from 75 psi to 95 psi Minimum Above 97.5% HP rpm 95 psi Trent XWB-75, -79, -79B and -84 with Service Bulletin 73-J148 or Modification 73-J148 Incorporated Minimum Ground idle to 70% HP rotor rpm 25 psi Minimum between 70% and 93% HP rpm increasing linearly from 25 psi to 43 psi Minimum between 93% and 96.0% HP rpm increasing linearly from 43 psi to 75 psi Minimum between 96.0% and 97.0% HP rpm 75 psi Minimum between 97.0% and 97.5% HP rpm increasing linearly from 75 psi to 95 psi Minimum Above 97.5% HP rpm 95 psi Trent XWB-75EP, -79EP, -79BEP and -84EP Minimum Ground idle to 70.4% HP rotor rpm 25 psi Minimum between 70.4% and 93.6% HP rpm increasing linearly from 25 psi to 41 psi Minimum between 93.6% and 96.3% HP rpm increasing linearly from 41 psi to 48 psi Minimum between 96.3% and 98.5% HP rpm increasing linearly from 48 psi to 72 psi Minimum Above 98.5% HP rpm 95 psi Trent XWB-97 Trent XWB-97 without Service Bulletin 73-K304 Incorporated: Minimum Ground idle to 75% HP rotor rpm 25 psi Minimum between 75% and 91.8% HP rpm increasing linearly from 25 psi to 42 psi Minimum between 91.8% and 95.0% HP rpm increasing linearly from 42 psi to 75 psi Minimum Above 95.0% HP rpm 75 psi Trent XWB-97 with Service Bulletin 73-K304 Incorporated: Minimum Ground idle to 75% HP rotor rpm 25 psi Minimum between 75% and 96% HP rpm increasing linearly from 25 psi to 45 psi Minimum between 96% and 97.7% HP rpm increasing linearly from 45 psi to 75 psi Minimum Above 97.7% HP rpm 75 psi TCDS E00086EN Page 7 of 14 NOTE 4. ACCESSORY DRIVE MOUNTING PROVISIONS: The engine’s accessory gearbox may be fitted with two, Variable Frequency Generators (VFG) and two Hydraulic Pumps to provide electrical and hydraulic power to the aircraft. These units are part of the airframe, and certified under Aircraft Airworthiness Standards. The Engine Installation Manual details installation and operational requirements, including torque and power limitations. Drive and mounting provisions Accessory VFG A VFG B Hydraulic Pump Green Circuit Hydraulic Pump Yellow Circuit Drive identification Rear face of external gearbox Front face of external gearbox Front face of external gearbox, inboard Front face of external gearbox, outboard Speed ratio 1.762 HP speed 1.726 HP speed 0.363 HP speed 0.363 HP speed Direction of rotation (looking at drive pad) Anti- Clockwise Anti- Clockwise Clockwise Clockwise Maximum power 122 kVA (172 kVA transient) 122 kVA (172 kVA transient) 126 HP 166 HP Maximum torque 703.9 Nm 703.9 Nm 974.0 Nm 974.0 Nm Overhung moment 124 Nm 124 Nm 51.1 Nm 51.1 Nm NOTE 5. MODEL DESCRIPTION: Trent XWB-75 and -75EP Same as Trent XWB-84 except for decreased thrust ratings. Trent XWB-79 and -79EP Same as Trent XWB-84 except for decreased thrust ratings. Trent XWB-79B and 79BEP Same as Trent XWB-79 except flat rated to ISA + 21.6ºC. Trent XWB-84 and -84EP Baseline engine configuration. Trent XWB-97 Same as Trent XWB-84 except for increased thrust ratings, increased turbine entry temperature and a two-minute transient overtemperature limit. NOTE 6. TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS, PROVIDED AS PART OF ENGINE TYPE DESIGN: Not Applicable 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: See NOTE 21 NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS: The engine mount points are on the Fancase, Intercase and Tail Bearing Housing and are defined in the Engine Installation Manual NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS: Not Applicable TCDS E00086EN Page 8 of 14 NOTE 11. SPECIAL INSTALLATION REQUIREMENTS: ETOPS: Trent XWB-75, -75EP, -79, -79EP, -79B, -79BEP, -84, and -84EP These models have demonstrated eligibility for ETOPS under 14 CFR §33.201 for a maximum diversion time of 420 minutes. The Trent XWB-75, Trent XWB-75EP, Trent XWB-79, Trent XWB-79EP, Trent XWB-79B, Trent XWB-79BEP, Trent XWB-84 and Trent XWB-84EP engine models have complied with the requirements of §§ 33.4 (A33.3(c)), 33.71(c)(4) and 33.201, and are therefore eligible for installation on Extended Operations (ETOPS) and Early ETOPS approved airplanes. The demonstrated diversion time is 405 minutes at MCT plus 15 minutes at hold power. Note, that ETOPS eligibility does not constitute airplane or operational level approvals necessary to conduct ETOPS flights. Trent XWB-97 with Service Bulletin 72-K939 Incorporated This model has demonstrated eligibility for ETOPS under 14 CFR §33.201 for a maximum diversion time of 420 minutes. The Trent XWB-97 engine model has complied with the requirements of §§ 33.4 (A33.3(c)), 33.71(c)(4) and 33.201, and is therefore eligible for installation on Extended Operations (ETOPS) and Early ETOPS approved airplanes. The demonstrated diversion time is 405 minutes at MCT plus 15 minutes at hold power. Note, that ETOPS eligibility does not constitute airplane or operational level approvals necessary to conduct ETOPS flights. THRUST REVERSER: Trent XWB-75, -79, -79B and -84 These engines are approved for use in thrust reverse operation with Goodrich thrust reverser system: 351-3000-513 –LH Wing – TRU Assy 351-3000-515 –RH Wing – TRU Assy Trent XWB-75EP, -79EP, -79BEP and -84EP These engines are approved for use in thrust reverse operation with Goodrich thrust reverser system: 351-3000-601 –LH Wing – TRU Assy 351-3000-603 –RH Wing – TRU Assy Trent XWB-97 These engines are approved for use in thrust reverse operation with Goodrich thrust reverser system: 351-3000-505 –LH Wing – TRU Assy 351-3000-507 –RH Wing – TRU Assy Maximum reverse thrust should not be used below 60 KCAS at which point idle reverse thrust should be promptly selected. Reverse thrust should be fully deselected below 40 KCAS. EMISSIONS STANDARDS: 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 the Trent XWB-75, -75EP, - 79, -79EP, -79B, -79BEP, -84, -84EP and -97. Fuel Venting Emission Standards: 14 CFR §§ 34.10(a) and 34.11, and 40 CFR §§ 1031.30(b) Smoke Number (SN) Emission Standards: 14 CFR §34.21(e)(2) and 40 CFR § 1031.60(a)(5) Carbon Monoxide (CO) Emission Standards: 14 CFR § 34.21(d)(1)(ii) and 40 CFR § 1031.60(d) Hydrocarbons (HC) Emission Standards: 14 CFR § 34.21(d)(1)(i) and 40 CFR § 1031.60(e) Oxides of Nitrogen (NOx) Emission Standards: 14 CFR § 34.23(b)(1) and 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, Rolls-Royce 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.3 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 been demonstrated. TCDS E00086EN Page 9 of 14 NOTE 11. continued TIME LIMITED DISPATCH: Criteria pertaining to the engine control systems’ dispatch and maintenance requirements for Trent XWB engine models are specified in the Airworthiness Limitations Section of the Time Limits Manual (See NOTE 15), and also in the following reports, which define the various configurations and maximum operating intervals: • For Trent XWB-75, -79, -79B and -84: Document number JXW001/1889, issue 4; “Trent XWB: Dispatchability Summary” • For Trent XWB-75EP, -79EP, -79BEP and -84EP: Document number JXW003/0666, issue 2; “Trent XWB-84EP: Dispatchability Summary” • For Trent XWB-97: Document number JXW002/1125, issue 2; “ Trent XWB-97 in the Trent XWB: Dispatchability Summary XWB-97” ENGINE GAS TEMPERATURE: The measured Engine Gas Temperature (EGT) is modified by trimming for the purposes of the cockpit display. Trimming of EGT is done to provide consistent cockpit displayed levels of maximum allowable EGT, across engine models irrespective of the maximum allowable levels of un-trimmed EGT. EGT trims are programmed into the Data Entry Plug (DEP) which is fitted to the Electronic Engine Controller (EEC). The EEC processes the EGT and calculates the indicated EGT. Indicated redline values and corresponding EGT pull-down trims are provided in the following tables. Trent XWB-75, -79, -79B and -84 Redline Value EGT Indicated [°C] EGT Pull-down [°C] Maximum Continuous 850 -85 Take-off 900 -93 20 second Over Temperature 920 -80.5 Trent XWB-75EP, -79EP, -79BEP and -83EP Redline Value EGT Indicated [°C] EGT Pull-down [°C) Maximum Continuous 850 -48.5 Take-off 900 -54 20 second Over Temperature 920 -35.5 Trent XWB-97 Redline Value EGT Indicated [°C] EGT Pull-down [°C] Maximum Continuous 850 -130.5 Take-off 900 -137 Take-off (2 minute transient) -152 20 second Over Temperature 920 -137.5 NOTE 12. MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF INTEREST: Service bulletins, structural repair manuals, vendor manuals, and engine maintenance manuals, which contain a statement that the document is approved by the European Aviation Safety Agency, are accepted by the FAA and are considered FAA approved. These approvals pertain to the design data only. NOTE 13. SPECIAL OPERATING PROCEDURES: 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. Some engine models are approved for 2-minute transient overtemperature within 5-minute time limit associated with the take-off rating when engine is accelerated to take-off from a cold state. The engine is approved for a maximum exhaust gas overtemperature of 920oC for inadvertent use due to abnormal operation for periods up to 20 seconds without requiring rejection of the engine from service or maintenance action other than to correct the cause. The cause of the overtemperature must be investigated and corrected. TCDS E00086EN Page 10 of 14 NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS: Not Applicable NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE AND OVERHAUL MANUALS. Trent XWB manuals submitted under EASA requirements and accepted as equivalent to 14 CFR § 33.4 and 14 CFR § 33.5 requirements are: Trent XWB-75, -79, -79B and -84 OPERATING INSTRUCTIONS INSTALLATION MANUAL ENGINE MANUAL TIME LIMITS MANUAL OI-TRENT-XWB- A350-900 EDNS01001308950 TRENTXWB-K0680- EMAN0-01 TRENTXWB-K0680- TIME0-01 Trent XWB-75EP, -79EP, -79BEP and -84EP OPERATING INSTRUCTIONS INSTALLATION MANUAL ENGINE MANUAL TIME LMITS MANUAL OI-TRENT-XWB- A350-900 EDNS01001308950 TRENTXWB-K0680- EMAND-01 TRENTXWB-K0680- TIMED-01 Trent XWB-97 OPERATING INSTRUCTIONS INSTALLATION MANUAL ENGINE MANUAL TIME LIMITS MANUAL OI-Trent XWB-97- A350 EDNS01000583229 TRENTXWB-K0680- EMANB-01 TRENTXWB-K0680- TIMEB-01 Trent XWB-75, -79, -79B, -84 and -97 Cleaning, Inspection, and Repair Manual (CIR) Check and Rectify Manual (CRM) Standard Practices Manual (SPM) Overhaul Processes Manual (OPM) TRENTXWB-K0680- CIRM0-01 TRENTXWB-K0680- CREP0-01 RR-CAEL-SPM TSD594-J Trent XWB-75EP, -79EP, -79BEP and -84EP Cleaning, Inspection, and Repair ManuaL (CIR) Check and Rectify Manual (CRM) Standard Practices Manual (SPM) Overhaul Processes Manual (OPM) TRENTXWB-K0680- CIRMD-01 TRENTXWB-K0680- CREPD-01 RR-CAEL-SPM TSD594-J Trent XWB-75, -79, -79B, -84 and -97 Maintenance Manual Split Engine Transportation Airbus A350 Customer Aircraft Maintenance Manual TRENTXWB-K0680- SETM0-01