# TCDS E00086EN: Rolls-Royce Deutschland Ltd & Co KG

- Type: Type certificate data sheet
- Status: Current
- Holder: Rolls-Royce Deutschland Ltd & Co KG
- Revision: 9
- Revised: June 30, 2026
- Product: Engine
- Certification basis: Part 33, Part 21
- Registered aircraft: 38, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/cc/4d/cc4d38eb0344345fe12732450919f56ea7dfaf760f35976d3c2521d527a7073c
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID144752331120260630213336.0001
- Page: https://openairdocs.org/tcds/E00086EN

## Models (9)

As the data sheet lists them.

- Trent XWB-75
- Trent XWB-79
- Trent XWB-79B
- Trent XWB-84
- Trent XWB-97
- Trent XWB-75EP
- Trent XWB-79EP
- Trent XWB-79BEP
- Trent XWB-84EP

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
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 
  
 
Trent XWB-75EP, -79EP, -79BEP and -84EP 
Maintenance Manual Split Engine 
Transportation 
Airbus A350 Customer 
Aircraft Maintenance 
Manual 
TRENTXWB-K0680-
SETMD-01 
 
All Trent XWB 
Civil Large Engines Engine Oils Manual 
EOM-CIVIL-1RR 
 
All Trent XWB 
Civil Engines Engine Fuels Manual 
PMC-ROLLSROYCEFUEL-K0680 EFMC0-01

TCDS E00086EN Page 11 of 14 
 
NOTE  16.  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 E00086EN, is in a condition for safe 
operation and has undergone a final operational check. 
 
Reference 14 CFR Section 21.500, which provides for the airworthiness acceptance of aircraft engines 
manufactured outside of the U.S. and 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." 
NOTE  17. LIFE LIMITED PART INFORMATION: 
Life-limited parts are identified in Time Limits Manuals identified in NOTE 15. 
The Trent XWB cyclic life limits are based on a commercial mission cycle, which consists of a start, takeoff, 
climb, cruise, descent, and landing.  Use (or non-use) of a fan reverser for braking during landing does not affect 
cycle counts.  Each of the following constitutes one cycle: 
(1) a flight consisting of a takeoff and landing, 
(2) a touch-and-go landing or simulated touch-and-go landing (no weight on wheels) for pilot training. 
NOTE  18. MILITARY MODEL INFORMATION:   
Not applicable. 
NOTE  19. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS (%): 
100% HP = 12,600 rpm; 100% IP = 8,200 rpm; 100% LP = 2,700 rpm 
When maintenance running is performed above idle thrust with the aircraft static, the control system 
automatically applies a temperature dependent LP speed limit (Keep Out Zone).  Refer to the Aircraft 
Maintenance Manual for details.   
The Maximum Continuous speeds are not displayed as limitations on the aircraft flight deck. 
 
Trent XWB-75, -79, -79B and -84 
  LP IP HP 
 Without Service 
Bulletin 73-J148 
Incorporated 
 98.1% 100% 97.4% 
Takeoff (5 
minutes) 
With Service Bulletin 
73-J148 Incorporated 
(4.2.1 Software) 
 99.1% 
Post SB 72-H706 (Mk2 
Fan) 
98.1% 
Pre SB 72-H706 (Mk1d 
Fan)   
100% 97.4% 
 With Service Bulletin 
73-K228 Incorporated 
(6.1.1 Software or later 
approved software 
version) 
 99.1% 
Post SB 72-H706 (Mk2 
Fan) 
98.1% 
Pre SB 72-H706 (Mk1d 
Fan) 
100.2% 98.6% 
Maximum 
Continuous 
All  96.8% 98.5% 96.4%

TCDS E00086EN Page 12 of 14 
 
NOTE  19. 
continued 
Trent XWB-75EP, -79EP, -79BEP and -84EP 
Takeoff (5 minutes) 
 HP   98.6% 
 IP 101.2% 
 LP   98.6% 
 
Maximum Continuous  
 HP   96.2% 
 IP   99.3% 
 LP   97.7% 
 
Trent XWB-97 
  LP IP HP 
 Without Service 
Bulletin 73-K304 
Incorporated 
104.3% 102.6% 99.8% 
Take-off (5 
minutes) 
With Service 
Bulletin 73-K304 
Incorporated 
(XWB_97-7.0 
Software) 
104.3% 102.6% 99.9% 
 With Service 
Bulletin 73-K698 
Incorporated 
(XWB-97_13.0 
Software or later 
approved software 
version) 
104.3% 102.6% 102.2% 
Maximum 
Continuous 
Without Service 
Bulletin 73-K140 
Incorporated 
102.4% 100% 98.5% 
 With Service 
Bulletin 73-K140 
Incorporated 
(Profile 4) 
101.7% 100% 97.9% 
 
Stabilized operation in the speed range shown below (ISA day) is not permitted during all ground operations. 
The EEC software includes a logic which does not permit stabilized operation in this speed range as appropriate 
for the ambient conditions. However, passing through the above speed range, while increasing or decreasing 
thrust is permitted. 
 
Trent XWB-75, -79, -79B and -84 
Without Service 
Bulletin 73-K228 
Incorporated 
With Service Bulletin 
73-K228 Incorporated 
(6.1.1 Software) 
With Service Bulletin 73-
K386 Incorporated (10.1 
Software) 
With Service Bulletin 
73-L309 or 73-L310 
Incorporated (16.2 
Software or later 
approved software 
version) 
71.5% to 79.7% 68.6% to 79.7% 67% to 79.7% 66.8% to 79.7% 
 
Trent XWB-75EP, -79EP, -79BEP and -84EP 
 66.8% to 79.7% 
Trent XWB-97 
 64% to 84%     
NOTE 20.  OUTPUT/PROPELLER SHAFT TORQUE LIMITS: 
Not Applicable

TCDS E00086EN Page 13 of 14 
 
NOTE 21. 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS: 
Airframe ventilation (Cabin Bleed) is modulated via a regulating valve. 
 
Trent XWB-75, -79, -79B and -84 
Engine Power Setting  Maximum Normal Cabin Air Bleed 
Turbine Entry Temperature (TET (K)) % Core Mass Flow (W26) 
1000    11.00 (HPC 6) 
1415    11.00 (HPC 6) 
1716    4.9 (HPC 6/IPC 8) 
1786 and above   2.1 (IPC 8) 
 
Engine Power Setting  Maximum Abnormal Cabin Air Bleed 
TET (K)    % Core Mass Flow (W26) 
1000    14.6 (HPC 6) 
1485    14.6 (HPC 6) 
1685    12.8 (HPC 6) 
1720    10.4 (HPC 6/IPC 8) 
1750    6.5 (IPC 8) 
1815 and above   3.7 (IPC 8) 
 
Nacelle thermal anti-icing flow demand (HPC3) is modulated via a regulating valve. 
 
Engine Power Setting  Maximum Cowl Thermal Anti Ice Flow 
TET (K)    % Core Mass Flow (W30) 
1000    1.00 
1256    1.00 
1685    0.97 
1815 and above   0.45 
 
Trent XWB-75EP, -79EP, -79BEP and -84EP 
Engine Power Setting  Maximum Normal Cabin Air Bleed 
Turbine Entry Temperature (TET (K)) % Core Mass Flow 
800    11.2 (W26)(HPC 6) 
1484    6.7 (W24)(IPC 8) 
1687    3.3 (W24)(IPC 8) 
1793    2.2 (W24)(IPC8) 
1815 and above   1.8 (W24)(IPC 8) 
 
Engine Power Setting  Maximum Abnormal Cabin Air Bleed 
TET (K)    % Core Mass Flow) 
800    14.9 (W26)(HPC 6) 
1555    14.9 (W26)(HPC 6) 
1589    14.2 (W24)(IPC 8) 
1704    5.5 (W24)(IPC 8) 
1737    5.1 (W24)(IPC 8) 
1784    4.1 (W24)(IPC 8) 
1808    3.4 (W24)(IPC 8) 
1810 and above   3 (W24)(IPC 8) 
 
Engine Power Setting  Maximum Cowl Thermal Anti Ice Flow 
TET (K)    % Core Mass Flow (W26) 
800    1.2 (HPC3) 
1268    1.2 (HPC3) 
1350    1.1 (HPC3)  
1708     0.8 (HPC3) 
1805 and above   0.3 (HPC3)  
Trent XWB-97 
Engine Power Setting  Maximum Normal Cabin Air Bleed 
TET (K))    % Core Mass Flow (W26) 
1000    10.80 (HPC 6) 
1575    10.80 (HPC 6) 
1675    6.60 (HPC 6) 
1744.9    4.9 (HPC 6) 
1745    4.00 (IPC 8) 
1886 and above   2.6 (IPC 8)

TCDS E00086EN Page 14 of 14 
 
NOTE 21. 
continued  
 
Engine Power Setting  Maximum Abnormal Cabin Air Bleed 
TET (K)    % Core Mass Flow (W26) 
1000    14.1 (HPC 6) 
1685    14.1 (HPC 6) 
1790    13.5 (HPC 6) 
1814.9    9.9 (HPC 6/IPC 8) 
1815    3.9 (IPC 8) 
1886 and above   3.1 (IPC 8) 
 
Nacelle thermal anti-icing flow demand (HP3) is modulated via a regulating valve. 
 
Engine Power Setting  Maximum Cowl Thermal Anti Ice Flow 
TET (K)    % Core Mass Flow (W30) 
1000    0.80 
1431    0.80 
1810.9    0.76 
1811    0.40 
1900 and above   0.30 
 
W26 and W30 represent the air mass-flow through the core of the engine. 
 
NOTE 22.  ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT (WHERE SPECIAL REQUIREMENTS 
APPLY): 
 
Trent XWB-75, -79, -79B and -84 
See Exemption to § 33.27(f)(6), No. 15079 dated February 29, 2016, for applicable conditions and limitations. 
 
Trent XWB-97 
See Exemption to § 33.27(f)(6), No. 17441 dated August 16, 2017, for applicable conditions and limitations. 
 
NOTE 23. These engines are fitted with a Digital Electronic Engine Fuel Control system in which the software is 
designated as follows according to EUROCAE ED-12B/RTCA DO178B: 
 
• EEC:  Level “A”. 
• EMU:  Level “E”, except that the flight deck vibration display is Level “C”. 
 
 
----END----
```

## ADs (12, in force first)

- [AD 2026-13-06](https://openairdocs.org/ad/2026-13-06): Engine (Turbine/Turboprop), Engine Fuel Distribution · Rolls-Royce Deutschland Trent XWB-75, Trent XWB-79, Trent XWB-79B and 2 more. Effective Jul 17, 2026
- [AD 2024-20-08](https://openairdocs.org/ad/2024-20-08): Engine (Turbine/Turboprop) · Rolls-Royce Deutschland Trent XWB-97. Effective Nov 8, 2024
- [AD 2023-04-14](https://openairdocs.org/ad/2023-04-14): Engine Mount Sector · Rolls-Royce Deutschland Trent XWB-75, Trent XWB-79, Trent XWB-79B and 2 more. Effective Apr 14, 2023
- [AD 2022-13-17](https://openairdocs.org/ad/2022-13-17): Engine Turbine/Turboprop · Rolls-Royce Deutschland Trent XWB-75, Trent XWB-79, Trent XWB-79B and 2 more. Effective Aug 12, 2022
- [AD 2021-17-11](https://openairdocs.org/ad/2021-17-11): Turbine Engine Compressor Section · Rolls-Royce Deutschland Trent XWB-75, Trent XWB-79, Trent XWB-79B and 1 more. Effective Oct 12, 2021
- [AD 2020-16-17](https://openairdocs.org/ad/2020-16-17): Turbine Section · Rolls-Royce Deutschland Trent XWB-75, Trent XWB-79, Trent XWB-79B and 1 more. Effective Sep 21, 2020
- [AD 2020-12-03](https://openairdocs.org/ad/2020-12-03): Engine (Turbine/Turboprop) · Rolls-Royce Deutschland Trent XWB-97. Effective Jun 18, 2020
- [AD 2017-19-19](https://openairdocs.org/ad/2017-19-19): Turbine Engine Compressor Section · Rolls-Royce Trent XWB-75, Trent XWB-79, Trent XWB-79B and 1 more. Effective Oct 11, 2017
- [AD 2017-17-07](https://openairdocs.org/ad/2017-17-07): Turbine/Turboprop Engine/Turbine Section · Rolls-Royce Trent XWB-75, Trent XWB-79, Trent XWB-79B and 1 more. Effective Sep 12, 2017
- [AD 2024-25-10](https://openairdocs.org/ad/2024-25-10) (historical): Engine (Turbine/Turboprop); Engine Fuel Distribution · Rolls-Royce Deutschland Trent XWB-97. Effective Feb 18, 2025
- [AD 2021-15-01](https://openairdocs.org/ad/2021-15-01) (historical): Engine Turbine/Turboprop · Rolls-Royce Deutschland Trent XWB-75, Trent XWB-79, Trent XWB-79B and 2 more. Effective Aug 16, 2021
- [AD 2020-12-01](https://openairdocs.org/ad/2020-12-01) (historical): Engine Mount Section · Rolls-Royce Deutschland Trent XWB-75, Trent XWB-79, Trent XWB-79B and 1 more. Effective Jul 13, 2020

## Registered aircraft by registry model (OpenAirDocs)

- [Rolls-Royce TRENT XWB-84](https://openairdocs.org/engine/rolls-royce-trent-xwb-84): 35 aircraft (registry code 54599)
- [Rolls Deu TRENT XWB-84](https://openairdocs.org/engine/rolls-deu-trent-xwb-84): 3 aircraft (registry code 54600)

---
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