# TCDS E39NE: Rolls-Royce Deutschland Ltd & Co KG

- Type: Type certificate data sheet
- Status: Current
- Holder: Rolls-Royce Deutschland Ltd & Co KG
- Revision: 8
- Revised: August 6, 2024
- Product: Engine
- Certification basis: Part 21, Part 33
- Data sheet PDF: https://openairdocs.org/files/sha256/1c/62/1c6226de125676c4e9c76a7428c2abe4c6bf92f835ba33bf091b82f4f7dc5833
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID129565078520240808133423.0001
- Page: https://openairdocs.org/tcds/E39NE

## Models (3)

As the data sheet lists them.

- RB211 Trent 768-60
- RB211 Trent 772-60
- RB211 Trent 772B-60

## What the data sheet says

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

```text
Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E39NE) 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 E39NE to  
     Rolls-Royce Deutschland on February 21, 2019 
 
 
I. MODELS RB211 Trent 
768-60 
RB211 Trent 
772-60 
RB211 Trent 
772B-60  
TYPE 
 
 
 
 
RATINGS (See NOTE 1) 
 
Maximum continuous 
Thrust pounds at sea level static 
 
Takeoff (5 minutes) 
Thrust pounds at sea level static 
Equivalent bare engine thrust 
High by-pass turbofan (by-pass ratio of 5.17:1 for  the 768-60  and  5.05:1  for  the 
772-60  and  772B-60),  axial  flow,  three-shaft.   Single-stage  low  pressure  fan 
driven  by four 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. 
 
 
 
60410(2) 
 
 
 
63560(4) 
 
 
 
63560(4) 
 
 
67500(1) 
 
71100(3) 
 
71100(5)(6) 
68400 72000 72000 
(1) 
(2) 
 
 
(3) 
 
(4) 
 
(5) 
 
 
 
(6) 
Flat rated to ISA + 15oC for all altitudes. 
ISA + 15oC up to 20,000 feet varying linearly to  
ISA +10oC at 25,000 feet ISA + 10oC above 25,000 
feet. 
ISA + 15oC up to 8,000 feet varying linearly to ISA + 
10oC at 10,000 feet  ISA + 10oC above 10,000  feet.  
ISA + 15oC up to 5,000 feet varying linearly to ISA + 
10oC at 10,000 feet ISA + 10 oC above 10,000 feet. 
ISA + 22oC up to 2,000 feet varying linearly to ISA + 
15oC at 5,000 feet ISA + 15oC up to 8,000 feet varying 
linearly to ISA + 10oC at 10,000 feet ISA 10oC above 
10,000 feet. 
The Trent 772B-60 has the same ratings as the 772-60 
except between 2,000 ft and 8,000 ft altitude or when   
the ambient temperature is greater than ISA +15oC, 
where the 772B-60 produces  increased thrust at take-  
off ratings. The magnitude of this increase varies with 
altitude and ambient temperature and is limited to a 
maximum of 5.4%. 
 
* 
PAGE 1 2 3 4 5 6 7 8 
REV. 8 1 8 6 5 5 8 5 
 
 TCDS NUMBER E39NE 
U.S. DEPARTMENT OF TRANSPORTATION  REVISION:   8 
 DATE: August 6, 2024 
FEDERAL AVIATION ADMINISTRATION   
 ROLLS-ROYCE, Deutschland Ltd. & Co. KG 
TYPE CERTIFICATE DATA SHEET E39NE  
 MODELS: 
 RB211 TRENT 768-60 
 RB211 TRENT 772-60 
 RB211 TRENT 772B-60 
 
LEGEND: "- -" INDICATES "SAME AS PRECEDING 
MODEL" "---" NOT APPLICABLE 
NOTE: SIGNIFICANT CHANGES IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN.

TCDS E39NE PAGE 2 
 
 
 
I. MODELS RB211 Trent 
768-60 
RB211 Trent 
772-60 
RB211 Trent 
772B-60  
PRINCIPAL DIMENSIONS, inches 
Length 
From front fan case flange to rear of CNA 
Radius,  maximum 
CENTER OF GRAVITY - complete 
powerplant 
Aft from powerplant station 100 
Below centerline 
Stbd.  from  engine centerline 
CENTER OF GRAVITY - basic engine 
Aft from powerplant station 100 
Below centerline 
Stbd. from engine centerline 
WEIGHT 
Dry Powerplant 
Basic Engine 
 
 
ENGINE PARTICULARS BUILD STND 
RR Drawing Introduction Sheet (DIS) 
 
 
222 
54 
 
 
- - 
- - 
 
 
- - 
- - 
 
 
28.2 
1.4 
0.1 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
 
25.4 
1.6 
0.2 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
 
14368 
11023 
 
- - 
- - 
 
- - 
- - 
 
Basic engine is the dry powerplant less nacelle, intake, cowl doors, CNA and 
thrust reverser. 
 
2150 
Issue 4 
 
2141 
Issue 3 
 
2179 
Issue 1 
 
 
FUELS 
APPROVED FUELS 
 
OILS    
APPROVED OILS 
OIL CONSUMPTION 
OIL CAPACITY 
Nominal total system capacity 
Nominal oil tank capacity 
Minimum useable oil (including effect of 
attitude) 
 
 
 
COMPONENTS 
 
ELECTRONIC FULL AUTHORITY FUEL 
CONTROL 
Fuel control 
Fuel pump 
Fuel metering unit 
IGNITION SYSTEM 
Ignition system plugs 
Ignition system units 
EQUIPMENT 
 
See relevant Engine Operating Instructions for approved oils. 
1.42 U.S. pints/hour overall inflight maximum for unrestricted  operation.  
 
93.9 U.S. pints 
49.2 U.S. pints 
32.5 U.S. pints 
 
- - 
- - 
- - 
  
 
RB211 Trent 
768-60 
RB211 Trent 
772-60 
RB211 Trent 772B-60 
 
 
 
 
Lucas EEC 2000-03AB1 
Argotech 721400 
Lucas FMU 700 MK1 
 
 
 
 
- - 
- - 
- - 
 
 
 
 
Lucas EEC 2000-06BE1 
- - 
- - 
 
Champion CH34691 
Simmonds 430081 
 
- - 
- - 
 
- - 
- - 
For identification of equipment approved for use on these engines, refer to 
Chapter 1 of appropriate Rolls-Royce Drawing Introduction Sheet (DIS).

TCDS E39NE PAGE 3 
 
 
 
CERTIFICATION BASIS 14 CFR 21.29 and 14 CFR part 33 effective February 1, 1965, amendments 33- 1 through  33-15. 
Pursuant to 14 CFR 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 was found to    
provide a level of safety equivalent to that provided by 14 CFR part 33, amendment 33-15. 
 
 
MODEL        APPLICATION        ISSUED/ DELETED 
            DATE        REVISED
      
RB211 TRENT 768-60 
RB211 TRENT 772-60 
RB211  TRENT  772B-60 
FEB 12 1992 
FEB 12 1992 
MAR 2, 1998 
NOV 1, 1994 
NOV 1, 1994 
OCT 9, 1998 
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 
E39NE. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began 
oversight of this product on behalf of the UK.  
 
 
 
 
 
IMPORT 
REQUIREMENTS 
The following models comply with 14 CFR part 34, amendment 7A , effective May 24, 2024. See 
NOTE 11 for detailed summary of the certification basis for fuel venting and exhaust emissions: 
RB211 TRENT 768-60; RB211 TRENT 772-60; and RB211 TRENT 772B-60. 
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 E39NE, 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." 
 
NOTES Notes 1 through 20, which follow. 
 
 
 
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 ATF12161 or 
approved  alternatives. 
(4) Engine exhaust system defined by Common Nozzle Assembly (CNA) FK16544, Jet Pipe FK 16545, and 
Tail Plug FK 16507. 
(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. 
NOTES

TCDS E39NE PAGE 4 
 
 
NOTE 2. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS  (%) 
 
100% HP = 10,611 RPM 
100% IP = 7,000 RPM 
100% LP = 3,900 RPM 
 
Maximum takeoff (5 minutes) (See NOTES 18, 19 and 20)  
HP 100.0 
IP 103.3 
LP 99.0 
Maximum overspeed (20 seconds) 
HP 100.0 
IP 103.3 
LP 99.0 
Maximum reverse thrust (30 seconds) 
LP 80.8 
 
NOTE 3. MAXIMUM   PERMISSIBLE   TEMPERATURES 
TURBINE GAS TEMPERATURE (TGT) oC 
Starting 
Below 50% N3 (ground starting) 
Below 50% N3 (inflight starting) 
Above 50% N3 
Takeoff (5 minutes) 
 
Maximum continuous (unrestricted) 
Overtemperature (20 seconds) 
 
 
 
 
 
 
700 Momentary max. during start or relight 
850 
850 
900 May be used up to 10 minutes in the event of one engine 
failure. 
850 
920 
 
Fuel 
Maximum temperature at outlet from HP fuel pump (oC) 
Unrestricted 
Max. during transient overshoots on reducing 
rpm (15 min. limit) 
120 
 
140 
 
Oil 
Combined scavenge temperature (oC) 
Minimum  for starting 
Minimum for opening up 
Maximum for unrestricted use 
 
 
 
-40 
50 
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 acceptance for flight 
Ground idle to 70% HP rpm 
Above 95% HP rpm 
Minimum to complete flight 
Ground idle and 70% HP rpm 
Above 95%  HP rpm 
 
 
35 psig 
60 psig 
 
24 psig 
50 psig

TCDS E39NE PAGE 5 
 
 
NOTE 5. MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS 
 
Air delivery  for  aircraft  services,  excluding powerplant  anti-icing.  The  air  is  automatically scheduled  from the 
engine IP stage 8 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), IP compressor delivery 
pressure (P25) and altitude together  with  a  synthesized  HP  compressor  delivery temperature    (T30Syn). 
 
With valve controller ABG SEMCA DRG 6764A010000 the switchover from the HP to the IP compressor delivery      
port  occurs  at  engine power  settings  where the following  conditions  are met: 
(a) T30Syn is greater than 450oC + 2.5oC and P30 is greater than 75 psi + 2.5 ambient pressure or 
(b) Altitude is greater than 26,000 ft + 250 and P30 is greater than 85 psi + 2.5 ambient pressure or 
(c) P25 is greater than 40 psi + 4.0 ambient pressure. 
 
 
Maximum HP6 bleed, (% of gas generator compressor flow); This bleed decreases linearly between the values listed  
below  for  the low  idle and  switchover points. 
 
1. Normal operation: 
i. Low Idle 
ii. At switchover point (1.26 EPR) 
2. Abnormal (one engine inoperative): 
i. Low Idle 
ii. At switchoverpoint (1.26 EPR) 
 
 
11.6 
5.2 
 
12.7 
5.8 
 
Maximum IP8 bleed (5 of gas generator compressor flow); This bleed (IP8) decreases linearly between the values   
listed  below  for  the switchover  and  maximum  continuous points) 
 
1. Normal operation: 
i. At switchover point 
ii. Max. continuous 
iii. Above max. continuous 
2. Abnormal (one engine inoperative): 
i. At switchover point 
ii. Max. continuous 
iii. Above max. continuous 
 
 
4.5 
3.1 
2.4 
 
5.3 
4.0 
2.9 
 
Maximum LP bleed (% of fan flow) 
 
1. Normal & Abnormal (one engine inoperative): 
i. From low idle to max. continuous 
ii. Above max. continuous 
 
1.23 
0.96 
 
Maximum HP3 bleed for powerplant anti-icing (% of HPC inlet flow); This bleed decreases linearly between the  
values  listed  below  for  the 1450K TET and  max.  continuous points) 
 
1. Normal & Abnormal (one engine inoperative): 
i. From low idle to 1450K TET 
ii. Max. continuous 
iii. Above max. continuous 
 
 
0.75 
0.69 
0.44

TCDS E39NE PAGE 6 
 
 
 
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 IN- 
STANTANEOUS  
OVERHANG 
(IN - LB) 
ALL 
MODELS 
STARTER 
IDG 
HYDRAU 
LIC 
PUMPS 
Rear 
pump 
Front 
pump 
CW 
CW 
 
CW 
CW 
1.00057 
0.855 
 
0.4002 
0.3919 
SEE BELOW 
2956 
 
1500 
1500 
SEE BELOW 
5000 
 
1730 
1730 
290 
1300 
 
183 
183 
  CW = CLOCKWISE 
CCW = COUNTERCLOCKWISE 
 
Max starter torque varies with air temperature as follows:  
Air temperature (oC) Max torque (lb - in) 
10 
-20 
-40 
7440 
8640 
10800 
 
NOTE 7. Power settings, power check, and control of the engine output is to be based on Rolls-Royce (RR) engine charts   
included in RR Operating Instructions referring to engine pressure ratio (EPR). Pressure probes are included in the  
engine for this purpose. 
 
NOTE 8. Life limited parts are identified in the Engine Manual. 
 
NOTE 9. This engine approval includes bare engine plus thrust reverser, engine mounting feet and links, core engine 
cowlings, and engine accessories, coolers, filters, harness, and instrumentation transmitters as defined in the 
appropriate RR DIS.  Hydraulic pumps and IDG are aircraft supply. 
 
NOTE 10. RB211 series manuals under CAA requirements accepted as equivalent to 14 CFR 33.4 and 14  CFR 33.5 
requirements are: 
 
MODEL RB211- OPERATING 
INSTRUCTIONS 
MAINTENANCE 
MANUAL 
INSTALLATION 
MANUAL 
ENGINE 
MANUAL 
TRENT 768-60 
TRENT 772-60 
F-TRENT-A330 
F-TRENT-A330 
M-TRENT-A330 
M-TRENT-A330 
EL 2837 
EL 2837 
E-TRENT-IRR 
E-TRENT-IRR 
TRENT 772B-60 F-TRENT-A330 M-TRENT-A330 EL 2837 E-TRENT-1RR 
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.

TCDS E39NE PAGE 7 
 
 
NOTE 11.           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: RB211 TRENT 768 -60; RB211 TRENT 772-
60; and RB211 TRENT 772B-60. 
 
Fuel Venting Emission Standards: 14 CFR §§ 34.10(a) and 34.11; in addition, 40 CFR 1031.30(b).  
Smoke  Number  (SN)  Emission  Standards: 14  CFR  34.21(e)(2); in  addition,  40 CFR 1031.60(a)(5). 
Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 1031.60(d). 
Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 1031.60(c). 
Oxides of Nitrogen (NOX) Emission Standards: 14 CFR 34.23(b)(1); in addition, 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, the     
engine  manufacturer  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 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 also been demonstrated. 
 
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-178A/ED12A. 
 
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 21.4 percent. 
 
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 basis as defined in this Data Sheet when operating with the FADEC in 
reversionary control mode. 
 
NOTE 16. VARIANTS 
 
RB211 Trent 768-60 
RB211 Trent 772-60 
RB211  Trent 772B-60 
Basic model. 
Same as basic model except for increased thrust rating. 
Same as 772-60 model except for increased takeoff thrust ratings at altitude between 
2,000  feet  and  8,000 feet. 
 
NOTE 17. The RB211 Trent 700 series engines have been approved to operate with certain faults present in the control system,  based 
on satisfaction of 14 CFR part 33 requirements and appropriate 14 CFR part 25 control system reliability requirements. 
 
The following criteria exist as dispatch and maintenance requirements for the engine control system.  
 
Fault Class 1 Level A: 
Fault Class  1  Level B: 
 
Fault Class 2: 
No dispatch allowed 
Dispatchable; maximum operating interval for Fault Class 1 level B 
fault(s) is 150 operating hours 
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 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 no more than 5 minutes. 
 
NOTE 19. Post modification 73-C780, the maximum Take-off speeds for the LP and HP shafts are increased to 99.5% and 
100.7% respectively. The speed signals transmitted to the aircraft, however, are trimmed in order to maintain the    
same cockpit indicated Maximum Take-off speeds as the pre-modification standard, i.e., 99.0% and 100.0%.

TCDS E39NE PAGE 8 
 
 
NOTE 20. Post modification 73-E502 for the data entry plug for the selection of increased HP redline speed, the maximum 
take-off speed for the HP shaft is increased to 101.7%. However the speed signal transmitted to the aircraft is   
trimmed to maintain the same cockpit indication as the pre mod standard i.e. 100.0%. 
 
 
----END----
```

## ADs (56, first 50, in force first)

- [AD 2026-20-11](https://openairdocs.org/ad/2026-20-11): Turbine Engine Compressor Section · Rolls-Royce Deutschland RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Nov 17, 2026
- [AD 2026-18-04](https://openairdocs.org/ad/2026-18-04): Turbine Engine Compressor Section · Rolls-Royce Deutschland RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Oct 16, 2026
- [AD 2026-18-51](https://openairdocs.org/ad/2026-18-51): Turbine Engine Oil System · Rolls-Royce Deutschland RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Sep 21, 2026
- [AD 2026-10-06](https://openairdocs.org/ad/2026-10-06): Turbine Section · Rolls-Royce Deutschland RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Jun 12, 2026
- [AD 2023-17-12](https://openairdocs.org/ad/2023-17-12): Turbine Engine Compressor Section · Rolls-Royce Deutschland RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Oct 26, 2023
- [AD 2021-08-01](https://openairdocs.org/ad/2021-08-01): Turbine Engine Combustion Section · Rolls-Royce Deutschland RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Apr 30, 2021
- [AD 2017-10-13](https://openairdocs.org/ad/2017-10-13): Low-pressure (LP) fuel return tube · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Jul 10, 2017
- [AD 2017-10-06](https://openairdocs.org/ad/2017-10-06): Turbine Engine Compressor Section · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Jun 9, 2017
- [AD 2016-04-13](https://openairdocs.org/ad/2016-04-13): Sealing sleeve · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Apr 19, 2016
- [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 2014-14-01](https://openairdocs.org/ad/2014-14-01): Electronic engine control (EEC) · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Aug 15, 2014
- [AD 2013-23-17](https://openairdocs.org/ad/2013-23-17): High-pressure (HP) and intermediate-pressure (IP) turbine discs · Rolls-Royce RB211-535E4-37, RB211-535E4-B-37, RB211-535E4-C-37 and 3 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 2012-25-08](https://openairdocs.org/ad/2012-25-08): High pressure/ intermediate pressure (HP/IP) turbine bearing support oil feed tube outer heat shield · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Jan 10, 2013
- [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 2011-08-10](https://openairdocs.org/ad/2011-08-10): Oil metering jet · Rolls-Royce RB211 Trent 768-60 and RB211 Trent 772-60. Effective Apr 27, 2011
- [AD 98-09-27 R1](https://openairdocs.org/ad/98-09-27-R1): Thrust Reverser Hinge · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Apr 11, 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 2010-07-09](https://openairdocs.org/ad/2010-07-09): Vent tubes; vent flow restrictor · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective May 7, 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 2008-24-03](https://openairdocs.org/ad/2008-24-03): High-pressure/intermediate-pressure (HP/IP) turbine bearing internal oil vent tube, scavenge tube, and tube heat shields; vent flow restrictor · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Dec 15, 2008
- [AD 2008-11-19](https://openairdocs.org/ad/2008-11-19): Bearing chamber sealing sleeve · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Jun 16, 2008
- [AD 2007-24-09](https://openairdocs.org/ad/2007-24-09): High pressure/intermediate pressure (HP/IP) turbine bearing oil feed tube · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Dec 14, 2007
- [AD 2007-22-08](https://openairdocs.org/ad/2007-22-08): IP Compressor Rotor stage 2-3 interstage spacer · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Nov 13, 2007
- [AD 2006-23-07](https://openairdocs.org/ad/2006-23-07): Fan blade annulus fillers · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Nov 22, 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 2005-14-09](https://openairdocs.org/ad/2005-14-09): Engine Electronic Controller (EEC) · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Jul 25, 2005
- [AD 2005-05-06](https://openairdocs.org/ad/2005-05-06): Engine electronic controllers (EECs) · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Mar 24, 2005
- [AD 2005-01-16](https://openairdocs.org/ad/2005-01-16): Low pressure compressor (LPC) fan blade · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Jan 28, 2005
- [AD 2004-05-31](https://openairdocs.org/ad/2004-05-31): Time Limits Manual · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Mar 29, 2004
- [AD 2003-22-03](https://openairdocs.org/ad/2003-22-03): Low pressure (LP) turbine nozzle vane case · Rolls-Royce RB211 Trent 768-60 and RB211 Trent 772-60. Effective Nov 14, 2003
- [AD 2003-18-09](https://openairdocs.org/ad/2003-18-09): High pressure (HP) compressor rotor shafts · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Sep 24, 2003
- [AD 2000-24-24](https://openairdocs.org/ad/2000-24-24): Common Nozzle Assembly · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Jan 12, 2001
- [AD 2000-04-22](https://openairdocs.org/ad/2000-04-22): Rolls-Royce RB211-524G2-T-19, RB211-524G3-T-19, RB211-524H2-T-19 and 2 more. Effective Apr 7, 2000
- [AD 2000-02-17](https://openairdocs.org/ad/2000-02-17): Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Feb 16, 2000
- [AD 2020-24-08](https://openairdocs.org/ad/2020-24-08) (historical): Turbine Section · Rolls-Royce Deutschland RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Jan 4, 2021
- [AD 2020-06-16](https://openairdocs.org/ad/2020-06-16) (historical): Turbine Engine Compressor Section · Rolls-Royce Deutschland RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective May 5, 2020
- [AD 2017-03-02](https://openairdocs.org/ad/2017-03-02) (historical): LP compressor blade · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Mar 22, 2017
- [AD 2015-17-19](https://openairdocs.org/ad/2015-17-19) (historical): Fan case low-pressure (LP) fuel tube · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Oct 20, 2015
- [AD 2015-04-03](https://openairdocs.org/ad/2015-04-03) (historical): High- pressure/intermediate-pressure (HP/IP) turbine support internal oil feed tube · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Mar 30, 2015
- [AD 2014-16-10](https://openairdocs.org/ad/2014-16-10) (historical): LP compressor blades · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Sep 23, 2014
- [AD 2013-15-10](https://openairdocs.org/ad/2013-15-10) (historical): Cracking on the IP compressor rotor shaft rear balance land · Rolls-Royce RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17 and 22 more. Effective Oct 8, 2013
- [AD 2013-12-01](https://openairdocs.org/ad/2013-12-01) (historical): LP compressor blades · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Jul 29, 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 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 2007-02-05](https://openairdocs.org/ad/2007-02-05) (historical): High pressure-and-intermediate pressure (HP-IP) turbine internal and external oil 
vent tubes · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Feb 6, 2007
- [AD 2006-23-11](https://openairdocs.org/ad/2006-23-11) (historical): High pressure (HP)/intermediate pressure (IP) turbine bearing oil feed tube 
heat shield · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Dec 19, 2006
- [AD 2006-05-03](https://openairdocs.org/ad/2006-05-03) (historical): High pressure-intermediate pressure (HP- IP) turbine · Rolls-Royce RB211 Trent 768-60, RB211 Trent 772-60 and RB211 Trent 772B-60. Effective Mar 27, 2006

All 56: https://openairdocs.org/tcds/E39NE/ads.md

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