# TCDS E00050EN: Rolls-Royce Deutschland Ltd & Co KG

- Type: Type certificate data sheet
- Status: Current
- Holder: Rolls-Royce Deutschland Ltd & Co KG
- Revision: 9
- Revised: April 25, 2019
- Product: Engine
- Certification basis: Part 21, Part 33
- Data sheet PDF: https://openairdocs.org/files/sha256/1b/68/1b6861f24337a4ce3393273ea18b25db950c5b018809fb36053e3b494a1a5bd5
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/B96828C869C0EE298625847A0050DBBC.0001
- Page: https://openairdocs.org/tcds/E00050EN

## Models (7)

As the data sheet lists them.

- RB211-Trent 875-17
- RB211-Trent 884B-17
- RB211-Trent 877-17
- RB211-Trent 892B-17
- RB211-Trent 892-17
- RB211-Trent 895-17
- RB211-Trent 884-17

## 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” 
  
 
 
 
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” 
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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----
```

## ADs (51, first 50, in force first)

- [AD 2026-18-52](https://openairdocs.org/ad/2026-18-52): Turbine Engine Oil System · Rolls-Royce Deutschland RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Sep 21, 2026
- [AD 2023-23-13](https://openairdocs.org/ad/2023-23-13): Turbine Engine Compressor Section · Rolls-Royce Deutschland RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Jan 4, 2024
- [AD 2023-18-01](https://openairdocs.org/ad/2023-18-01): Engine Fuel Pump · Rolls-Royce Deutschland RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Oct 30, 2023
- [AD 2022-09-10](https://openairdocs.org/ad/2022-09-10): Turbine Engine Compressor Section · Rolls-Royce Deutschland RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Jun 23, 2022
- [AD 2020-25-04](https://openairdocs.org/ad/2020-25-04): Engine Fireseals · Rolls-Royce Deutschland RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Jan 8, 2021
- [AD 2018-18-15](https://openairdocs.org/ad/2018-18-15): Turbine Engine Compressor Section · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Nov 1, 2018
- [AD 2017-08-11](https://openairdocs.org/ad/2017-08-11): Engine · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective May 30, 2017
- [AD 2016-25-10](https://openairdocs.org/ad/2016-25-10): High-pressure compressor (HPC) · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Jan 20, 2017
- [AD 2015-04-06](https://openairdocs.org/ad/2015-04-06): Electronic engine control (EEC) · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Apr 8, 2015
- [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 2014-13-02](https://openairdocs.org/ad/2014-13-02): LP turbine bearing support and exhaust case assembly · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Aug 5, 2014
- [AD 2013-19-21](https://openairdocs.org/ad/2013-19-21): Cracks in the HP compressor stage 1 and 2 disc posts · Rolls-Royce RB211-524G2-T-19, RB211-524G3-T-19, RB211-524H-T-36 and 19 more. Effective Nov 6, 2013
- [AD 2012-18-07](https://openairdocs.org/ad/2012-18-07): Low-pressure (LP) compressor blades · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Oct 29, 2012
- [AD 2012-17-04](https://openairdocs.org/ad/2012-17-04): IP turbine discs · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Oct 1, 2012
- [AD 2012-11-01](https://openairdocs.org/ad/2012-11-01): Engines · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Jun 15, 2012
- [AD 2012-04-14](https://openairdocs.org/ad/2012-04-14): Engine · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Apr 11, 2012
- [AD 2011-26-08](https://openairdocs.org/ad/2011-26-08): Engine fuel leaks · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Jan 24, 2012
- [AD 2011-22-07](https://openairdocs.org/ad/2011-22-07): Cracks in the front combustion liner · Rolls-Royce RB211-524G2-T-19, RB211-524G3-T-19, RB211-524H-T-36 and 11 more. Effective Nov 29, 2011
- [AD 2011-10-04](https://openairdocs.org/ad/2011-10-04): HP compressor stage 1 disc · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 4 more. Effective Jun 7, 2011
- [AD 2010-20-11](https://openairdocs.org/ad/2010-20-11): Titanium compressor shafts · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 7 more. Effective Oct 29, 2010
- [AD 2010-06-14](https://openairdocs.org/ad/2010-06-14): HP/IP turbine bearing oil vent tube · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 4 more. Effective May 3, 2010
- [AD 2010-07-01](https://openairdocs.org/ad/2010-07-01): Aircraft fuel system · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 15 more. Effective May 3, 2010
- [AD 2009-21-09](https://openairdocs.org/ad/2009-21-09): High-pressure (HP) compressor rotor rear stage 5 and 6 discs and cone shafts · Rolls-Royce RB211-Trent 892B-17, RB211-Trent 895-17, RB211-Trent 875-17 and 3 more. Effective Nov 20, 2009
- [AD 97-06-13 R1](https://openairdocs.org/ad/97-06-13-R1): Rescinds AD 97-06-13. · Rolls-Royce RB211-Trent-892B-17, RB211-Trent 875-17, RB211-Trent 877-17 and 2 more. Effective Oct 2, 2006
- [AD 2006-05-01](https://openairdocs.org/ad/2006-05-01): Oil filler cap assembly · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 15 more. Effective Mar 16, 2006
- [AD 2005-25-11](https://openairdocs.org/ad/2005-25-11): Low pressure (LP) compressor fan blades · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 4 more. Effective Jan 17, 2006
- [AD 2005-20-23](https://openairdocs.org/ad/2005-20-23): Dry film lubricant (DFL) · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 4 more. Effective Nov 8, 2005
- [AD 2005-01-15 R1](https://openairdocs.org/ad/2005-01-15-R1): Fan blade dovetail roots · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 4 more. Effective Oct 17, 2005
- [AD 2004-19-08](https://openairdocs.org/ad/2004-19-08): Critical life-limited parts · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 4 more. Effective Oct 27, 2004
- [AD 2004-13-11](https://openairdocs.org/ad/2004-13-11): Intermediate Pressure (IP) Compressor Rear Stubshaft and IP Turbine Shaft · Rolls-Royce RB211-Trent 892B-17, RB211-Trent 895-17, RB211-Trent 875-17 and 3 more. Effective Jul 30, 2004
- [AD 2001-26-11](https://openairdocs.org/ad/2001-26-11): Low Pressure Compressor Fan Blade Roots · Rolls-Royce RB211-Trent 892B-17, RB211-Trent 875-17, RB211-Trent 877-17 and 2 more. Effective Jan 30, 2002
- [AD 2021-26-11](https://openairdocs.org/ad/2021-26-11) (historical): Engine Fuel Pump · Rolls-Royce Deutschland RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Jan 3, 2022
- [AD 2016-24-08](https://openairdocs.org/ad/2016-24-08) (historical): Upper bifurcation fairing · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Jan 5, 2017
- [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 2012-10-12](https://openairdocs.org/ad/2012-10-12) (historical): Compressor rotor shafts · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 15 more. Effective Jun 29, 2012
- [AD 2012-06-23](https://openairdocs.org/ad/2012-06-23) (historical): LP compressor blades · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Apr 20, 2012
- [AD 2012-04-13](https://openairdocs.org/ad/2012-04-13) (historical): HP compressor stage 1 and 2 disc posts · Rolls-Royce RB211-524G2-T-19, RB211-524G3-T-19, RB211-524H-T-36 and 19 more. Effective Apr 11, 2012
- [AD 2012-04-01](https://openairdocs.org/ad/2012-04-01) (historical): Critical engine parts · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 4 more. Effective Mar 28, 2012
- [AD 2011-08-07](https://openairdocs.org/ad/2011-08-07) (historical): LP compressor blades · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 4 more. Effective Jun 7, 2011
- [AD 2011-09-07](https://openairdocs.org/ad/2011-09-07) (historical): High-pressure compressor (HPC) Stage 1 and 2 disc posts · Rolls-Royce RB211-524G2-T-19, RB211-524G3-T-19, RB211-524H-T-36 and 19 more. Effective Jun 7, 2011
- [AD 2009-24-05](https://openairdocs.org/ad/2009-24-05) (historical): Fuel pipes · Rolls-Royce RB211-Trent-884B-17, RB211-Trent-892B-17, RB211-Trent-895-17 and 4 more. Effective Jan 4, 2010
- [AD 2008-18-08](https://openairdocs.org/ad/2008-18-08) (historical): IP Compressor rotor · Rolls-Royce RB211-Trent 884B-17, RB211-Trent 892B-17, RB211-Trent 895-17 and 14 more. Effective Oct 14, 2008
- [AD 2005-01-15](https://openairdocs.org/ad/2005-01-15) (historical): Fan blade dovetail roots · Rolls-Royce RB211-Trent-844B-17, RB211-Trent-884B-17, RB211-Trent-892B-17 and 5 more. Effective Jan 28, 2005
- [AD 2004-15-02](https://openairdocs.org/ad/2004-15-02) (historical): LP Compressor Fan Blade · Rolls-Royce RB211-Trent-884B-17, RB211-Trent-892B-17, RB211-Trent-895-17 and 4 more. Effective Sep 1, 2004
- [AD 2003-16-18](https://openairdocs.org/ad/2003-16-18) (historical): Intermediate pressure (IP) turbine discs · Rolls-Royce RB211-Trent 892B-17, RB211-Trent 895-17, RB211-Trent 875-17 and 3 more. Effective Sep 22, 2003
- [AD 2003-15-06](https://openairdocs.org/ad/2003-15-06) (historical): HP compressor rotor rear stage 5 and 6 discs · Rolls-Royce RB211-Trent-844B-17, RB211-Trent-892B-17, RB211-Trent-895-17 and 4 more. Effective Sep 3, 2003
- [AD 2002-10-15](https://openairdocs.org/ad/2002-10-15) (historical): Low Pressure Compressor (LPC) Fan Blade Roots · Rolls-Royce RB211-Trent-892B-17, RB211-Trent-895-17, RB211-Trent 875-17 and 3 more. Effective Jul 2, 2002
- [AD 2002-11-08](https://openairdocs.org/ad/2002-11-08) (historical): Low Pressure Compressor (LPC) fan blade · Rolls-Royce RB211-Trent-895-17, RB211-Trent 875-17, RB211-Trent 877-17 and 2 more. Effective Jun 21, 2002
- [AD 2000-24-26](https://openairdocs.org/ad/2000-24-26) (historical): Fan Blade Roots Inspection · Rolls-Royce RB211-Trent-892B-17, RB211-Trent 875-17, RB211-Trent 877-17 and 2 more. Effective Feb 12, 2001
- [AD 98-19-21](https://openairdocs.org/ad/98-19-21) (historical): Fan Blade · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 1 more. Effective Oct 7, 1998

All 51: https://openairdocs.org/tcds/E00050EN/ads.md

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