# TCDS E00066EN: Rolls-Royce Deutschland Ltd & Co KG

- Type: Type certificate data sheet
- Status: Current
- Holder: Rolls-Royce Deutschland Ltd & Co KG
- Revision: 5
- Revised: March 2, 2022
- Product: Engine
- Certification basis: Part 21, Part 33
- Data sheet PDF: https://openairdocs.org/files/sha256/a5/8a/a58abc064f668a19e10b7ba1a897093232d7e2ec90fcdfcdb4d1dcc5b603c61f
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/50EE1514CE7C67998625882F0071D924.0001
- Page: https://openairdocs.org/tcds/E00066EN

## Models (5)

As the data sheet lists them.

- RB211 Trent 553-61
- RB211 Trent 556-61
- RB211 Trent 560A2-61
- RB211 Trent 553A2-61
- RB211 Trent 556A2-61

## 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" 
NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. 
 
 
U.S. DEPARTMENT OF TRANSPORTATION 
 
TCDS NUMBER: E00066EN 
REVISION: 5 
DATE: March 2, 2022 
ROLLS-ROYCE, Deutschland Ltd. & Co. KG 
MODELS: 
FEDERAL AVIATION ADMINISTRATION 
TYPE CERTIFICATE DATA SHEET 
E00066EN 
 RB211 TRENT 553-61 RB211 TRENT 553A2-61 
 RB211 TRENT 556-61 RB211TRENT 556A2-61 
 RB211 TRENT 560A2-61 
 
Engines of models described herein conforming with this data sheet, (which is part of Type Certificate Number E00066EN), 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 E00066EN to 
Rolls-Royce, Deutschland on February 21, 2019 
 
1. MODELS RB211 
Trent 553-61, 
553A2-61 
RB211 
Trent 556-61, 
556A2-61 
RB211 
Trent 560A2-61 
TYPE High by-pass turbofan (by-pass ratio of 8.5), axial flow, three-shaft. 
Single stage low pressure fan driven by a five stage turbine. Eight 
stage intermediate pressure compressor driven by a single stage 
turbine. Six stage high pressure compressor driven by a single 
stage turbine. Annular combustion chamber. 
RATINGS (See NOTE 1) 
 
Maximum Continuous   (1) 
Thrust pounds at sea level static 
 
Takeoff (5 minutes) (2) 
Thrust pounds at sea level static 
Equivalent bare engine thrust 
 
 
 
44359 
 
 
 
44359 
 
 
 
44359 
55780 58462 61902 
56655 59350 62740 
 (1) Flat rated to ISA +10ºC for all altitudes. 
(2) Flat rated to ISA +15ºC for all altitudes. 
 
 
 
 
 
 
 
 
* 
Page 1 2 3 4 5 6 7 
Revision 5 5 5 5 5 5 5

E00066EN Page 2 of 7 
 
 
See relevant Engine Operating Instructions for approved fuels. 
FUELS 
APPROVED FUELS 
 
1. MODELS (continued) RB211 
Trent 553-61, 
553A2-61 
RB211 
Trent 556-61 
556A2-61 
RB211 
Trent 560A2-61 
PRINCIPAL DIMENSIONS, inches 
 
Length 
From tip of spinner (minus 
rubbertip to tail bearing housing 
plug mount) 
Radius, maximum 
 
 
184.6 
 
 
66.5 
 
 
- - 
 
 
- - 
 
 
- - 
 
 
- - 
 
CENTER OF GRAVITY- complete 
   
powerplant    
Aft from powerplant station 100 27.1 - - - - 
Below centerline 1.9 - - - - 
Starboard from engine centerline 0.1 - - - - 
 
CENTER OF GRAVITY- basic engine 
   
Aft from powerplant station 100 27.8 - - - - 
Below centerline 2.2 - - - - 
Starboard from engine centerline 0.2 - - - - 
WEIGHT* 
   
Dry powerplant 13797 - - - - 
Basic engine 10930 - - - - 
*Basic engine is the dry powerplant less nacelle, intake, cowl doors, CNA and thrust reverser 
 
 
ENGINE PARTICULARS BUILD 553-61: 2207 556-61: 2208 560A2-61: 2233 
STANDARD 
RR Drawing Introduction Sheet (DIS) 
Issue 4 
553A2-61: 2230 
Issue 4 
556A2-61: 2231 
Issue 1 
 Issue 1 Issue 1  
 
 
OILS 
APPROVED OILS 
OIL CONSUMPTION 
 
See relevant Engine Operating Instructions for approved oils. 
1.32 U.S. pints/hour overall inflight maximum for unrestricted 
operation. 
OIL CAPACITY 
Nominal total system capacity 
Nominal oil tank capacity 
Minimum useable oil (including effect 
of attitude) 
 
84.5 U.S. pints 
49.0 U.S. pints 
33.8 U.S. pints 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
COMPONENTS RB211 Trent 553-61, 556-61, 553A2-61, 556A2-61, and 560A2-61 
ELECTRONIC FULL AUTHORITY 
FUEL 
Fuel control 
Fuel pump 
Fuel metering unit 
 
 
TRWEECS 500-04 
TRWTPS 500MK2 
TRWHMU 500MK2 
IGNITION SYSTEM 
Ignition system plugs 
Ignition system units 
 
Federal Mogul CH34761 
Unison 430154 
EQUIPMENT For identification of equipment approved for use on these engines, refer to Chapter 1 
of appropriate Rolls-Royce Drawing Introduction Sheet (DIS)

E00066EN Page 3 of 7 
 
N O T E S 
CERTIFICATION BASIS FAR 21.29 and FAR 33 effective February 1, 1965, as amended by FAR 33-1 through 33-19. 
Pursuant to FAR21.29(a)(1)(ii), the Type Certificate was issued in validation of the British Civil 
Aviation Authority Certification Standards JAR-E change 9 plus 
OP E/96/1 and E/97/1, which was found to provide a level of safety equivalent to that provided by 
FAR 33, Amendment 33-19. 
 
APPLICATION ISSUED/ 
MODEL DATE REVISED SURRENDERED 
 
RB211 TRENT 553-61 MAY 20, 1998 November 20, 2001 
RB211 TRENT 556-61 MAY 20, 1998 November 20, 2001 
RB211 TRENT 556B-61 JAN 25, 2000 November 20, 2001   January 18, 2021 
RB211 TRENT 560-61 MAY 20, 1998 November 20, 2001   January 18, 2021 
RB211 TRENT 553A2-61 January 3, 2003 September 16, 2003 
RB211 TRENT 556A2-61 January 3, 2003 September 16, 2003 
RB211 TRENT 556B2-61 January 3, 2003 September 16, 2003 January 18, 2021 
RB211 TRENT 560A2-61 January 3, 2003 September 16, 2003 
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  
E00066EN. Effective September 28, 2003, the European Aviation Safety Agency 
(EASA) began oversight of this product on behalf of the UK. 
 
Engine models RB211 TRENT 556B-61, RB211 TRENT 560-61, and RB211 TRENT 556B2-61 
are being removed from the TCDS per the EASA/TC Holder request because they were 
certificated/validated but never produced (not in service). 
IMPORT 
REQUIREMENTS 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 E00066EN, 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." 
 
Refer to the applicable bilateral agreement to verify eligibility for import into the United States of 
both new and used aircraft based on the scope of the agreement, to identify any required 
statements by the exporting authority on the export certificate of airworthiness (or equivalent 
document), and for procedures for coordinating exceptions to conformity statements on these 
documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements 
for issuance of an airworthiness certificate for imported aircraft. 
 
 
 
NOTE 1. The engine ratings are based on static test stand operation under the following A & B conditions: 
 
A. 
(1) Compressor inlet air at 59ºF and 29.92 Hg. 
(2) No aircraft accessory loads or optional air extraction. 
(3) 100% air intake recovery corrected from the datum air intake system defined by drawing 
ATF 16471 or approved alternatives. 
(4) Engine exhaust system defined by Common Nozzle Assembly RX95432-7 and Spacer 
Ring RX95425 
(5) Turbine gas temperature and rotor speed limitations are not exceeded. 
 
B. Equivalent Bare Engine Thrust (LBF) 
The equivalent bare thrust (lbf) is rated thrust excluding the losses of propulsion fan duct 
And thrust reverser and jet pipe washed by the fan stream. 
 
NOTE 2. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS (%) 
100% HP = 13,300  RPM 
100% IP   = 9,100 RPM 
100% LP = 3,900 RPM 
 
Maximum takeoff (5 minutes) (See NOTE 18) 
 
HP 97.4 % 
IP 99.4 % 
LP 92.5 %

E00066EN Page 4 of 7 
 
 
NOTE 2. (continued) Maximum overspeed (20 seconds) 
 
HP (non-declared) 
IP (non-declared) 
LP (non-declared) 
 
Maximum reverse thrust (30 seconds) 
 
 LP 69.0%  
NOTE 3. MAXIMUM PERMISSIBLE TEMPERATURES  
 TURBINE GAS TEMPERATURE (TGT) ºC  
 Starting   
 Below 50% N3 (ground starting) 700 max. during start or relight 
 Below 50% N3 (inflight starting) 850 
 Above 50% N3  850 
 Takeoff (5 minutes)  900 may be used up to 10 minutes in the event 
   of engine failure 
 Maximum continuous (unrestricted) 850 
 Overtemperature (20 seconds)  920 
 
Oil 
Combined scavenge temperature (ºC) 
Minimum for starting 
for engines incorporating Modification Bulletin 79-E065 -40 
for engines incorporating Modification Bulletin 79-D327 -20 
Minimum for opening up 20 
Maximum for unrestricted use 190 
 
 
NOTE 4. FUEL AND OIL PRESSURE LIMITS 
 
Fuel 
MINIMUM FUEL PRESSURE 
Between sea-level and 41,000 feet, not less than 5 psig plus true fuel vapor pressure, measured at 
inlet to engine LP fuel pump. 
 
Oil 
Minimum oil pressure 
Ground idle to 70% HP rpm 25 psig 
Above 95% HP rpm 40 psig 
 
 
NOTE 5. MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS 
 
Air delivery for aircraft services, excluding powerplant anti-icing. The air is automatically 
scheduled from the engine HP stage 1 and HP stage 6 compressor bleed ports via two valves in the 
aircraft ducting, which select the appropriate supply in response to signals sensing HP compressor 
delivery pressure (P30) together with a synthesized HP compressor delivery temperature (T30Syn). 
 
With valve controller 6853A020000X5 the switchover from the HP6 to the HP1 compressor 
delivery port occurs at engine power settings where the following conditions are met: 
 
A. Out of icing conditions: When both the HPC delivery static pressure (P30S) is greater 
than 105 psi ± 5 gauge. 
 
B. In icing conditions: When both the HPC delivery pressure (P30S) reaches 130 psi ±5 gauge 
and the HPC delivery temperature (T30syn) reaches 375ºC ± 5ºC.

E00066EN Page 5 of 7 
 
 
NOTE 5. (Cont’d) Maximum HP6 bleed (in percentage of gas generator compressor flow); this bleed 
decreases linearly between the values listed below for the low idle and switchover points. 
 
A. Normal operation:  
(1) Low Idle and up to 1190ºk TET 9.5 
(2) At switchover point 4.0 
B. Abnormal (one engine inoperative):  
(1) Low idle and up to 1210ºk TET 16.25 
(2) At 1400K TET 7.7 
(3) At switchover point 7.0 
 
 
Maximum HP1 bleed ( in percentage of gas generator compressor flow); this bleed  
(HP1) decreases linearly between the values  listed below  for the switchover  and 
1700ºk TET. 
A. Normal operation: 
(1) At switchover point 4.0 
(2) Up to1700ºk TET 1.0 
(3) At takeoff 1.0 
B. Abnormal (one engine inoperative): 
(1) At switchover point 
 
4.6 
(2) Up to 1700ºk TET 2.0 
(3) At takeoff 2.0 
 
 
Maximum LP bleed (% of fan flow) 
 
A. Normal and Abnormal (one engine inoperative):  
 (1) From low idle and up to 1130ºk TET .53 
 (2) Above 1650ºk TET 0.25 
 
Maximum HP3 bleed for powerplant anti-icing (% of HPC inlet flow); this bleed decreases linearly 
between the values listed below for the1000ºk TET and 1600ºk TET points. 
 
A. Normal and Abnormal (one engine inoperative): 
(1) From low idle to 1000ºk TET 1.75% 
(2) At 1600ºk TET and up to takeoff 1.5% 
 
NOTE 6. SHAFT POWER EXTRACTION LIMITATIONS 
Accessory drive provisions (continuous power as listed may be extracted under all engine operating conditions) 
MODELS DRIVE ROTATION 
(AS VIEWED 
FROM 
GEARBOX) 
SPEED 
RATIO TO 
HP ROTOR 
SPEED 
TORQUE (lb. - in.) 
CONTINUOUS MAXIMUM 
INSTANTANEOUS 
OVERHANG 
(in. - lb.) 
ALL STARTER  CW* .7967  6360 290 
MODELS  
IDG 
  
CW 
 
.6807 
 
2200 
 
4505 
 
1300 
 HYDRAULIC CW .3744 1500 2000 183 
 PUMP       
* CW = CLOCKWISE 
CCW = COUNTERCLOCKWISE 
 
 
Max starter torque at 0ft varies with air temperature as follows: 
Air temperature Max torque (lb. - in,) 
-54 6084 
-40 6077 
ISA 5980

E00066EN Page 6 of 7 
 
 
NOTE 7. 
 
NOTE 8. 
 
 
NOTE 9. 
 
 
 
 
NOTE 10. 
The Full Authority Digital Engine Controller controls power settings 
Life limited parts are identified in the Engine manual. 
 
This engine approval includes bare engine plus engine accessories, coolers, filters, harness, and 
instrumentation transmitters as defined in the appropriate RR DIS. Hydraulic pumps and IDG are 
aircraft supply. 
 
 
RB211 series manuals under CAA requirements accepted as equivalent to FAR 33.4 and FAR 
33.5 requirements are: 
 
MODEL 
RB211- 
OPERATING 
INSTRUCTIONS 
MAINTENANCE 
MANUAL 
INSTALLATION 
MANUAL 
ENGINE 
MANUAL 
TRENT 553-61 OI - TRENT - A340 M - TRENT - A340 DNS 62612 E - TRENT - A340 
TRENT 556-61 OI - TRENT - A340 M - TRENT - A340 DNS 62612 E - TRENT - A340 
TRENT 553A2-61 OI - TRENT - A340 M - TRENT - A340 DNS 62612 E - TRENT - A340 
TRENT 556A2-61 OI - TRENT - A340 M - TRENT - A340 DNS 62612 E - TRENT - A340 
TRENT 560A2-61 OI - TRENT - A340 M - TRENT - A340 DNS 62612 E - TRENT - A340 
 
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 Part 34. 
 
 
NOTE 12. The engine is fitted with a Digital Electronic Engine Fuel Control system in which the software 
meets the "critical" standard of RTCA DO-178B. 
 
 
NOTE 13.  In icing conditions, the engine may be operated satisfactorily at LP rotor speeds (N1) down to low 
idle. Minimum corresponding N1 at low idle for these engines is 17.6 percent in flight and 15.4 
percent for ground running. 
 
 
NOTE 14. These engines are fitted with an independent IP and LP spool overspeed governor. Dispatch with 
this item unserviceable is not permitted. 
 
 
NOTE 15. These engines satisfy the certification base as defined in this Data Sheet when operating with the 
FADEC in reversionary control mode

E00066EN Page 7 of 7 
 
 
NOTE 16. 
 
 
 
 
 
 
 
 
 
 
NOTE 17. 
VARIANTS 
 
RB211 TRENT 553-61 Basic model. 
RB211 TRENT 556-61 Same as basic model except for increased takeoff thrust rating. 
RB211 TRENT 553A2-61 A derivative of the RB211 TRENT 553-61 with improved fuel 
consumption. 
RB211 TRENT 556A2-61 A derivative of the RB211 TRENT 556-61 with improved fuel 
consumption. 
RB211 TRENT 560A2-61 A derivative of the RB211 TRENT 553-61 with increased takeoff 
thrust rating and improved fuel consumption. 
 
 
The RB211 TRENT 500 series engines have been approved to operate with certain faults present inthe 
control system, based on satisfaction of FAR 33 requirements and appropriate FAR 25 control system 
reliability requirements. 
 
The following criteria exist as dispatch and maintenance requirements for the engine controlsystem. 
Fault Class 1 Level A: No dispatch allowed 
 
Fault Class 1 Level B: Dispatchable; maximum operating interval for Fault 
Class 1 Level B fault(s) is 300 operating hours 
 
Fault Class 2: Dispatchable; maximum operating interval for Fault 
Class 2 fault(s) is 500 operating hours 
 
Fault levels Class 1 and 2 constitute Rolls-Royce nomenclature. 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. The takeoff 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 no more than 5 minutes. 
 
---END---
```

## ADs (24, in force first)

- [AD 2017-19-16](https://openairdocs.org/ad/2017-19-16): Turbine Engine Compressor Section · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Oct 13, 2017
- [AD 2017-03-03](https://openairdocs.org/ad/2017-03-03): Engine Oil Cooler · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Mar 17, 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 2014-13-03](https://openairdocs.org/ad/2014-13-03): Electronic engine control (EEC) software · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Jul 14, 2014
- [AD 2013-23-12](https://openairdocs.org/ad/2013-23-12): Low-pressure (LP) compressor fan blade set · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Dec 11, 2013
- [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 2011-13-04](https://openairdocs.org/ad/2011-13-04): RH fuel manifold · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Jul 11, 2011
- [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 2008-25-01](https://openairdocs.org/ad/2008-25-01): Low-pressure turbine (LPT) discs · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Dec 17, 2008
- [AD 2008-23-04](https://openairdocs.org/ad/2008-23-04): Intermediate pressure (IP) turbine blade · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Dec 1, 2008
- [AD 2008-11-16](https://openairdocs.org/ad/2008-11-16): Intermediate pressure compressor (IPC) drums · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Jul 7, 2008
- [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 2006-03-14](https://openairdocs.org/ad/2006-03-14): High pressure-and-intermediate pressure (HP-IP) turbine oil vent tubes · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Feb 24, 2006
- [AD 2006-03-03](https://openairdocs.org/ad/2006-03-03): HPT rear seal plate locking plugs · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Feb 16, 2006
- [AD 2004-05-30](https://openairdocs.org/ad/2004-05-30): Time Limits Manual · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Apr 2, 2004
- [AD 2003-22-02](https://openairdocs.org/ad/2003-22-02): High Pressure (HP) fuel tubes · Rolls-Royce RB211 Trent 556-61. Effective Nov 14, 2003
- [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 2013-05-18](https://openairdocs.org/ad/2013-05-18) (historical): Fuel tubes and fuel tube clips · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Apr 5, 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 2012-04-13](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 2012-02-04](https://openairdocs.org/ad/2012-02-04) (historical): Engine fuel leaks · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Feb 24, 2012
- [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 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 2007-19-10](https://openairdocs.org/ad/2007-19-10) (historical): Intermediate Pressure Compressor (IP Compressor) Drums · Rolls-Royce RB211 Trent 553-61, RB211 Trent 553A2-61, RB211 Trent 556-61 and 5 more. Effective Oct 3, 2007

---
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