# TCDS E30NE: Rolls-Royce Deutschland Ltd & Co KG

- Type: Type certificate data sheet
- Status: Current
- Holder: Rolls-Royce Deutschland Ltd & Co KG
- Revision: 5
- Revised: April 25, 2019
- Product: Engine
- Certification basis: Part 21, Part 33
- Registered aircraft: 4, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/ea/9d/ea9d32739800709b7ae8324ba8cf28011222553556d475f9f1b26a63d5a2064f
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/68FD35ACA0ED4BB48625847A005093D1.0001
- Page: https://openairdocs.org/tcds/E30NE

## Models (8)

As the data sheet lists them.

- RB211-524H-T-36
- RB211-524H-36
- RB211-524G2-19
- RB211-524G2-T-19
- RB211-524H2-T-19
- RB211-524G3-19
- RB211-524G3-T-19
- RB211-524H2-19

## What the data sheet says

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

```text
TCDS NUMBER E30NE  
 REVISION: 5  
 
U.S. DEPARTMENT OF TRANSPORTATION  
DATE:  April 25, 2019  
 
FEDERAL AVIATION 
ADMINISTRATION 
ROLLS-ROYCE, Deutschland Ltd. & Co. KG   
 
TYPE CERTIFICATE DATA SHEET E30NE  
MODELS:  
RB211-524G2-19 RB211-524G2-T-19 
 RB211-524G3-19 RB211-524G3-T-19  RB211-524H-36 RB211-524H-T-36  RB211-524H2-19 RB211-524H2-T-19 
 
Engines  of models described herein conforming with this data sheet (which is part of Type Certificate Number E30NE) and othe r 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, oper ated, 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 to TC E30NE to   
 Rolls-Royce, Deutschland on February 21, 2019 
 
 
I. MODELS RB211-524G2-19/ 
524G2-T-19 
RB211-524G3-19/ 
524G3-T-19 
RB211-524H- 
36/524H-T-36 
RB211- 
524H2-19/ 
524H2-T-19 
 
TYPE 
 
 
 
RATINGS (See NOTE 1) 
 
Maximum continuous 
Thrust, pounds net at sea level static 
Equivalent bare engine thrust* 
 
Takeoff (5 minutes, see NOTE 18) 
Thrust, net pounds at sea level static 
Equivalent bare engine thrust* 
High by-pass turbofan (by-pass ratio of 4.3:1) , axial flow, three -rotor. Single-stage low pressure 
fan driven by three -stage turbine. Seven -stage intermediate pressure compressor driven by single 
stage turbine. Six -stage high pressure compressor driven by single turbine. Annular combustion 
chamber. 
 
 
47,230 ISA+10oC 
 
 
 
- - 
 
 
 
- - 
 
 
 
- - 
 
48,160 - - - - - - 
 
56,870 (1) 
 
- -(2) 
 
59,450(3) 
 
- - 
58,000 - - 60,600 - - 
1. ISA+15oC up to sea level, varying linearly to ISA+10oC at 5,000 ft; ISA+10oC at and above 
5,000 ft. 
2. Same as (1) except that up to +2.9% thrust is available at ISA+21.2oC between 0.1 and 0.4 
mach at 600 ft. 
3. ISA+15oCup to 1,400 ft., varing linearly to +8 oC between 1,400 ft. and 3,300 ft.; ISA+8 oC 
between 3,300 and 5,700 ft.; ISA+11.7oC above 5,700 ft.. 
*The equivalent bare engine thrust (lbf) is derived  from the rated thrust by excluding the losses of 
the propulsion fan duct and thrust reverser and jet pipe washed by the fan stream.  
 
PRINCIPAL DIMENSIONS, inches  
Length 
From front flange case 
to rear of INA 
Radius, maximum 
CENTER OF GRAVITY, inches  
Aft front suspension 
centerline Below 
centerline 
Port from engine centerline  
 
 
 
 
 
 
 
 
 
 
 
187.35 in. 
57.5 in. 
 
 
- - 
- - 
 
 
- - 
- - 
 
 
- - 
- - 
 
 
34.9 in. 
 
- - 
 
- - 
 
- -  
1.4 in. - - - - - - 
1.3 in. - - - - - - 
 
PAGE 1 2 3 4 5 6 7    
REV. 5 3 4 2 2 2 3   
 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" 
"---" NOT APPLICABLE

I. MODELS RB211- 
524G2-19/ 
524G2-T-19 
RB211- 
524G3-19/ 
524G3-T-19 
RB211- 
524H-36/ 
524H-T-36 
RB211- 
524H2-19/ 
524H2-T-19 
 
WEIGHT (LBS) 12,731/ - -/ - -/ 12,764/  
 12,540 - - - - 12,573  Dry powerplant weight less intake, intake systems, cowl doors, and cowl door support structure. 
ENGINE PARTICULARS BUILD STANDARD       
RR Drawing Introduction Sheet (DIS)  
2110/ 
 
2116/ 
 
2082/ 
 
2118/ 
 2186 2187 2189 2188  
FUELS  
APPROVED FUELS See relevant Engine Operating Instructions for approved fuels.  
 
OILS  
APPROVED OILS 
OIL CAPACITY (U.S. pints) 
Nominal total system capacity 
Nominal oil tank capacity 
Minimum usable oil (including effect of 
attitude) 
See relevant Engine Operating Instructions for approved oils. 
 
87.2 
56.9 
47.5 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
 
COMPONENTS RB211-524G2-19/ 
524G2-T-19 
RB211-524G3-19/ 
524G3-T-19 
RB211-524H- 
36/ 524H-T-36 
RB211- 
524H2-19/ 
524H2-T-19 
 
ELECTRONIC FULL AUTHORITY      
FUEL CONTROL     Fuel control Lucas FAFC 2000 - - - - - - 
Fuel pump and governor Lucas PAG 100 - - - - - - 
Fuel metering unit Lucas FMU 600 - - - - - - 
IGNITION SYSTEM      
Ignition system plugs Smiths 2701 RIG-1 - - - - - - 
Ignition system units Simmons 44760 - - - - - - 
EQUIPMENT For identification of equipment approved for use on these engines, refer to Chapter 1 of 
appropriate Rolls-Royce Drawing Introduction Sheet (DIS).  
 
CERTIFICATION BASIS FAR 21.29 and FAR 33 effective February 1, 1965, as amended by FAR 33-1 through 33-11. Pursuant to 
FAR 21.29(a)(1)(ii), the Type Certificate was issued in validation of the British Civil Aviation Authority 
(BCAR) Certification Standards Section C, Issue 13 (JAR-E Change 6), which were found to provide a level 
of safety equivalent to that provided by FAR 33, Amendment  33-11. 
 
 
MODEL 
APPLICATION 
DATE 
ISSUED/ 
REVISED 
 
DELETED 
RB211-524G-19 
RB211-524G2-19 
RB211-524G3-19 
RB211-524H-36 
RB211-524H2-19 
RB211-524G2-T-19 
RB211-524G3-T-19 
RB211-524H-T-36 
RB211-524H2-T-19 
AUG 28, 1986 
JAN 23, 1989 
MAY 09, 1989 
AUG 09, 1989 
SEP 19, 1989 
NOV 04, 1996 
NOV 04, 1996 
NOV 04, 1996 
NOV 04, 1996 
JUN 08, 1988 
FEB 28, 1989 
AUG 14, 1989 
OCT 06, 1989 
JAN 23, 1990 
OCT 02, 1997 
OCT 02, 1997 
OCT 02, 1997 
OCT 02, 1997 
MAY 20, 1998 
 
The United Kingdom Civil Aviation Authority originally type certificated this engine. The FAA validated 
this product under U.S. Type Certificate Number E30NE. Effective September 28, 2003, the European 
Aviation Safety Agency (EASA) began oversig ht of this product on behalf of 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 Civil Aviation Authority of United Kingdom 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 c onforms to the type design approved under the U.S. Type 
Certificate E30NE, 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 Ci vil 
Aircraft, Engines, Propellers, and Related Products Imported into the United States."  
 
 
NOTE 1. The engine ratings are based on static test stand operation under the following conditions: 
 
(1) Fan inlet air at 50oF 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 
Drawing JRH1794 or approved alternatives. 
(4) Engine exhaust system defined by Fan Thrust Reverser TR537 and Jet Pipe JP520. 
(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 = 3,900 rpm.  
 
Takeoff (5 minutes, see NOTE 18)  
HP 99.2 
IP 108.8 (for the -524H2-T-19) 
107.7 (all other models) 
LP 110.5 
Maximum continuous (unrestricted)  
HP 97.1 
IP 106.1 (for the -524H2-T-19) 
105.0 (all other models) 
LP 109.5 
 
Maximum overspeed (20 seconds)  
HP 100.9 (for the -524G/H-T) 
101.5 (all other models) 
IP 110.6 (for the -524H2-T-19) 
109.5 (all other models) 
LP 111.5 
 
Maximum reverse thrust (40 seconds)  
 
 
NOTE 3. 
LP 91.0 
MAXIMUM PERMISSIBLE TEMPERATURES 
TURBINE GAS TEMPERATURE (TGT) oC 
 Below 50% N3 (no time restriction) 
Above 50% N3 the following apply: 
Takeoff (5 minutes, see NOTE 18) 
600 
 
785 
 Maximum continuous (unrestricted) 733 
 Overtemperature (20 seconds) 805 
 OIL 
Combined scavenge 
 
Minimum for starting Minus 30oC 
Minimum for opening up Minus 10oC 
Maximum for unrestricted use 171oC 
NOTES

NOTE 4. FUEL AND OIL PRESSURE LIMITS 
FUEL 
MINIMUM FUEL PRESSURE  
Between sea level and 45,00 feet, not less than 5 psig plus true fuel vapor pressure with zero vapor/liquid 
ratio.  Measured at inlet to engine LP fuel pump.  
 
OIL 
Measured between secondary oil pump and internal gearbox scavenge oil return line. 
Normal 
Between ground idle and 70% HP rpm 35 - 150 psid 
Above 70% HP rpm 40 - 150 psid 
 
Minimum to complete flight  
Ground idle to 70% HP rpm 25 psid 
Above 70% HP rpm 35 psid 
 
Large reductions in engine rpm to below 70% HP rpm may result in transient reductions in oil pressure 
below 25 psid. This is acceptable provided the oil pressure does not fall below 18 psid and recovers to at 
least 25 psid within 5 minutes of throttling ba ck. 
 
NOTE 5. MAXIMUM PERMISSIBLE AIR BLEEDS 
 
 
 
 
 
RB211-524G-19/G2-19/G3- 
19/H2-19/G2-T-19/G3-T- 
19/H2-T-19 
 
 
RB211-524H-36/H-T-36 
 
 
 
 
 
 
 
 
 
 
 
Maximum HP bleed, ground 
idle to changeover point 
(percent of gas generator 
compressor flow) 
 
Maximum IP bleed (percent 
of gas generator compressor 
flow). Decreases linearly 
with increases in HP 
compressor delivery 
pressure such that the bleed 
is: 
The engine bleed is automatically scheduled from the engine IP and HP ports by a switching valve in 
the aircraft ducting which selects from the appropriate port in response to a signal sensing HP 
compressor delivery pressure (P3.0).  
 
With valve controller 60B-40123-103, bleed air is extracted from the IP delivery port at engine 
power settings above that giving a P3.0 greater than 84 psig, plus or minus 3 psig, at sea level, and 
84 psig, plus or minus 4 psig, at 30,000 feet altitude, then decreasi ng linearly with ambient pressure 
to 71 psig, plus or minus 3 psig, at 45,000 feet altitude.  
 
Switching occurs at P3.0 of 105 psig, plus or minus 5 psig, at altitudes below 27,000 feet, decreasing 
linearly to 75 psig, plus or minus 5 psig, at 43,000 feet.  
 
At power settings below these switching pressures, bleed air is extracted from the HP bleed port.  
 
The nose cowl anti-icing air bleed flow, which is approximately 1.5% compressor flow, is included 
in the maximum bleed flows quoted for IP and HP bleeds.  
 
The compressor air bleeds are to be used in accordance with Rolls -Royce instructions and such that 
the operating limitations are not exceeded.  
 
Unrestricted. 
 
9.0 (524G2-19, 524G2-T-19, 524G3-19, 524G3-T-19, 524H2-19, 524H2-T-19) 
10.6 (524H036, 524H-T-36)

NOTE 5. Continued 
 
At the changeover point 
 
At max. continuous 
conditions 
At max. takeoff conditions 
 
Maximum LP bleed (% of fan 
flow) 
From ground idle to 93% 
HP rpm 
At max. continuous 
From max. continuous to 
maximum takeoff 
 
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)  
 
CONTINUOUS 
MAXIMUM 
INSTANTANEOUS 
OVERHANG 
(in.-lbs.) 
ALL 
MODELS 
STARTER 
IDG 
HYDRAULIC PUMP 
(for each of two 
drives) 
CCW 
CCW 
CCW 
1.0036 
0.8524 
0.3842 
15,300 
190 HP 
1,450 
19,320 
950 HP 5 secs 
7,250 
800 
1,750 
400 
  CW = CLOCKWISE 
CCW = COUNTERCLOCKWISE 
 
NOTE 7. Power settings, power check, and control of the engine output is to be based on integrated engine 
pressure ratio (IEPR). Pressure probes are included in the engine for this purpose. Maximum IEPR 
setting values relevant to each rating are contained in rating tables within the  FAFC. 
 
NOTE 8. Life-limited parts are identified in Time Limit Manual T-211(524)-7RR. 
 
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 pump, VSCF and IDG are aircraft supply. 
 
NOTE 10.  RB211 series manuals under BCAR requirements accepted as equivalent to FAR 33.4 and 33.5 
requirements are: 
 
MODEL RB211 OPERATING 
INSTRUCTIONS  
MAINTENANCE 
MANUAL 
INSTALLATION 
MANUAL 
ENGINE 
MANUAL 
524G2-19 F-211 (524G/H)-747 Boeing 747-400 D633U101-RR EL2806 A (B747) E211 (524)-7RR 
524G3-19 F-211 (524G/H)-747 Boeing 747-400 D633U101-RR EL2806 A (B747) E211 (524)-7RR 
524H-36 F-211 (524)-767 Boeing 767 D633T193 EL2812A (B767) E211 (524)-7RR 
524H2-19 F-211 (524G/H)-747 Boeing 747-400 D633U101-RR EL2806 A (B747) E211 (524)-7RR 
524G2-T-19 F-211 (524G/H)-747 Boeing 747-400 D633U101-RR EL2806 A (B747) E211 (524)-7RR 
524G3-T-19 F-211 (524G/H)-747 Boeing 747-400 D633U101-RR EL2806 A (B747) E211 (524)-7RR 
524H-T-36 F-211 (524)-767 Boeing 767 D633T193 EL2812A (B767) E211 (524)-7RR 
524H2-T-19 F-211 (524G/H)-747 Boeing 747-400 D633U101-RR EL2806 (B747) E211 (524)-7RR 
6.3 
 
5.0 
 
3.4 
 
 
0.6 
 
0.4 
 
0.6

NOTE 11. The RB211-524G/H engines comply with applicable exhaust emissions and fuel venting requirements 
of SFAR 27-5. The RB211-524G/H-t engines comply with SFAR 27 -5 and recommendations of ICAO 
Annex 16, Vol. 2, Second Edition 1993. 
 
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 satisfactorily at LP rotor speeds (N1) down to Low Idle. 
Minimum corresponding N1 at Low Idle for these engines is 24 percent.  
 
NOTE 14. These engines are fitted with an independent HP 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 FAFC 
in reversionary control mode. 
 
NOTE 16. VARIANTS 
 
The RB211-524G-19 was originally approved for installation in the B747 -400 aircraft on June 8, 1988. 
This variant is no longer in service and was deleted from  this TCDS at Revision 2.  
 
The RB211-524G2-19 is a variant of the existing RB211 -524G-19, incorporating a new rating plug in 
the FAFC to provide increased thrust during climb.  
 
The RB211-524G3-19 is a variant of the existing RB211 -524G-19, incorporating a new rating plug in 
the FAFC to provide and increase in thrust in part of the takeoff envelope.  
 
The RB211-524H-36 was originally approved for installation in the B767 -300 aircraft on October 6, 
1989. It is a variant of the existing RB211 -524G engine series with performance and installation 
changes to suit the B767-300 aircraft. 
 
The RB211-524H2-19 is a variant of the RB211-524H-36, with performance and installation changes to 
suit the B747-400 aircraft. 
 
The RB211-524G2-T-19, -524G3-T-19, -524H2-T-19 and -524H-T-36 are variants of the RB211 - 
524G2-19, -524G3-19, -524H2-19 and -524H-36 respectively and feature the RB211 -TRENT-700 04 
Module and accommodating modification (72 -CO67) to provide improved engine performance and 
reliability. 
 
NOTE 17.  The RB211-524G/H 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. 
 
The following criteria exist as dispa tch and maintenance requirements for the engine control system: 
Fault Level C:    No dispatch allowed  
Fault Level C1: Dispatchable; maximum operating interval for Fault Level C1 fault/s 
is 150 operating hours. 
 
Fault Level C2: Dispatchable; maximum operating interval for Fault Level C2 fault/s 
is 560 operating hours. 
 
Fault Levels C, C1, and C2 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.  
 
A control system reliability monitoring program has been established with Rolls -Royce in compliance 
with the reporting requirements as outlined in the Engine and Propeller Directorate Policy letter dated 
28 October 1993, for Time Limited Dispatch of engines fitted with FADEC Systems. Rolls -Royce will 
provide data reporting in accordance with Attachment 1, Paragraph 17, of the aforementioned policy 
letter, to the FAA Engine Certification Office, ANE -140, on a quarterly basis.

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 not more than 5 minutes. 
 
 
NOTE 19. Service Information: 
 
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 CAA (UK). 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.  
 
----END----
```

## ADs (44, in force first)

- [AD 2024-07-04](https://openairdocs.org/ad/2024-07-04): Turbine Engine Compressor Section · Rolls-Royce Deutschland RB211-524H-36 and RB211-524H-T-36. Effective Apr 15, 2024
- [AD 2023-22-01](https://openairdocs.org/ad/2023-22-01): Turbine Section · Rolls-Royce Deutschland RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 5 more. Effective Dec 26, 2023
- [AD 2023-21-03](https://openairdocs.org/ad/2023-21-03): Turbine Engine Compressor Section · Rolls-Royce Deutschland RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 5 more. Effective Dec 11, 2023
- [AD 2019-11-07](https://openairdocs.org/ad/2019-11-07): Turbine Engine Compressor Section · Rolls-Royce RB211-524G3-19, RB211-524G3-T-19, RB211-524H-36 and 3 more. Effective Jun 28, 2019
- [AD 2016-08-07](https://openairdocs.org/ad/2016-08-07): LPT support roller bearing · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 22 more. Effective May 16, 2016
- [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 2013-16-23](https://openairdocs.org/ad/2013-16-23): Cracked and distorted FCL metering panel · Rolls-Royce RB211-524B-02, RB211-524B2-19, RB211-524B3-02 and 13 more. Effective Oct 8, 2013
- [AD 2013-04-01](https://openairdocs.org/ad/2013-04-01): Thrust reverser units (TRUs) · Rolls-Royce RB211-524D4-19, RB211-524D4-39, RB211-524D4-B-19 and 11 more. Effective Mar 8, 2013
- [AD 2012-25-09](https://openairdocs.org/ad/2012-25-09): Intermediate-pressure (IP) turbine discs · Rolls-Royce RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 10 more. Effective Feb 6, 2013
- [AD 2011-18-21](https://openairdocs.org/ad/2011-18-21): Combustion liners · Rolls-Royce RB211-524B-02, RB211-524B2-19, RB211-524B2-B-19 and 19 more. Effective Feb 13, 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 2011-23-12](https://openairdocs.org/ad/2011-23-12): Fan blade · Rolls-Royce RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 5 more. Effective Nov 29, 2011
- [AD 2008-20-04](https://openairdocs.org/ad/2008-20-04): HP turbine discs · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 26 more. Effective Nov 3, 2008
- [AD 2008-16-18](https://openairdocs.org/ad/2008-16-18): High Pressure (HP) turbine disc · Rolls-Royce RB211-524B-02, RB211-524B-B-02, RB211-524B2-19 and 20 more. Effective Sep 15, 2008
- [AD 2006-11-05 R2](https://openairdocs.org/ad/2006-11-05-R2): High pressure compressor (HPC) · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 27 more. Effective Feb 21, 2008
- [AD 2007-14-07](https://openairdocs.org/ad/2007-14-07): Fluorescent penetrant inspections (FPI) · Rolls-Royce RB211-524B-02, RB211-524B-B-02, RB211-524B2-19 and 21 more. Effective Aug 16, 2007
- [AD 2007-06-10](https://openairdocs.org/ad/2007-06-10): Intermediate pressure compressor (IPC) stage 5 disks · Rolls-Royce RB211-524B-02, RB211-524B-B-02, RB211-524B2-19 and 20 more. Effective Apr 19, 2007
- [AD 2004-19-04](https://openairdocs.org/ad/2004-19-04): Critical Life-Limited Rotating Engine Parts · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 27 more. Effective Nov 1, 2004
- [AD 2004-01-21](https://openairdocs.org/ad/2004-01-21): Frount engine mount housing · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 27 more. Effective Feb 27, 2004
- [AD 2003-22-04](https://openairdocs.org/ad/2003-22-04): Low pressure (LP) compressor fan blade · Rolls-Royce RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 5 more. Effective Nov 12, 2003
- [AD 2003-21-11](https://openairdocs.org/ad/2003-21-11): High speed gearbox (HSGB) · Rolls-Royce RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 5 more. Effective Nov 10, 2003
- [AD 2003-14-23](https://openairdocs.org/ad/2003-14-23): High pressure compressor (HPC) rotor stage · Rolls-Royce RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 5 more. Effective Aug 1, 2003
- [AD 2002-02-12](https://openairdocs.org/ad/2002-02-12): Fan Blades · Rolls-Royce RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 5 more. Effective Mar 1, 2002
- [AD 2000-11-10](https://openairdocs.org/ad/2000-11-10): Rotor Shafts · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524-02 and 23 more. Effective Aug 7, 2000
- [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 2000-03-07](https://openairdocs.org/ad/2000-03-07): Rolls-Royce RB211-524H-36. Effective Mar 2, 2000
- [AD 86-15-01 R2](https://openairdocs.org/ad/86-15-01-R2): Stage 1 And 2 HPC Disk Assemblies · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 23 more. Effective Jul 1, 1987
- [AD 86-24-05](https://openairdocs.org/ad/86-24-05): Rotors And Disks Oversped · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 22 more. Effective Dec 20, 1986
- [AD 83-01-03](https://openairdocs.org/ad/83-01-03): Disk Assemblies · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 22 more. Effective Feb 17, 1983
- [AD 82-12-05](https://openairdocs.org/ad/82-12-05): Fan Assembly · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 22 more. Effective Jun 7, 1982
- [AD 75-16-09](https://openairdocs.org/ad/75-16-09): HS External Gearbox Oil Tank Filler Cap And Housing · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 22 more. Effective Aug 27, 1975
- [AD 75-16-08](https://openairdocs.org/ad/75-16-08): Intermediate and High Pressure Compressors · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 22 more. Effective Aug 22, 1975
- [AD 2020-15-07](https://openairdocs.org/ad/2020-15-07) (historical): Turbine Section · Rolls-Royce Deutschland RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 5 more. Effective Aug 4, 2020
- [AD 2013-26-10](https://openairdocs.org/ad/2013-26-10) (historical): High-pressure (HP) compressor rotor stage 1 and stage 2 discs · Rolls-Royce RB211-524G2-19, RB211-524G3-19, RB211-524H-36 and 1 more. Effective Jan 23, 2014
- [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 2011-13-01](https://openairdocs.org/ad/2011-13-01) (historical): Rivets · Rolls-Royce RB211-524D4-19, RB211-524D4-39, RB211-524D4-B-19 and 11 more. Effective Aug 12, 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 2006-11-05 R1](https://openairdocs.org/ad/2006-11-05-R1) (historical): Disc assemblies · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 27 more. Effective May 1, 2007
- [AD 2006-11-05](https://openairdocs.org/ad/2006-11-05) (historical): High pressure compressor (HPC) stage 3 disc assemblies · Rolls-Royce RB211-22B-02, RB211-524B-02, RB211-524B-B-02 and 24 more. Effective Jun 27, 2006
- [AD 2004-26-05](https://openairdocs.org/ad/2004-26-05) (historical): Head section and meterpanel assembly of the combustion liner · Rolls-Royce RB211-524B-02, RB211-524B-B-02, RB211-524B2-19 and 20 more. Effective Feb 9, 2005
- [AD 2004-01-20](https://openairdocs.org/ad/2004-01-20) (historical): High pressure compressor (HPC) · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 27 more. Effective Feb 24, 2004
- [AD 2000-05-12](https://openairdocs.org/ad/2000-05-12) (historical): Fan Blades · Rolls-Royce RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 4 more. Effective Mar 31, 2000
- [AD 97-07-04](https://openairdocs.org/ad/97-07-04) (historical): Combustor Liner · Rolls-Royce RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19 and 5 more. Effective Jun 6, 1997
- [AD 94-18-03](https://openairdocs.org/ad/94-18-03) (historical): Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524-02 and 23 more. Effective Sep 26, 1994

## Registered aircraft by registry model (OpenAirDocs)

- [Rolls-Royce RB211-524H-36](https://openairdocs.org/engine/rolls-royce-rb211-524h-36): 2 aircraft (registry code 54124)
- [Rolls-Royce RB211-524HT36](https://openairdocs.org/engine/rolls-royce-rb211-524ht36): 2 aircraft (registry code 54125)
- [Rolls-Royce RB211-524G219](https://openairdocs.org/engine/rolls-royce-rb211-524g219): 0 aircraft (registry code 54120)
- [Rolls-Royce RB211-524G319](https://openairdocs.org/engine/rolls-royce-rb211-524g319): 0 aircraft (registry code 54122)
- [Rolls-Royce RB211-524H219](https://openairdocs.org/engine/rolls-royce-rb211-524h219): 0 aircraft (registry code 54126)
- [Rolls-Royce RB211524G2T19](https://openairdocs.org/engine/rolls-royce-rb211524g2t19): 0 aircraft (registry code 54121)
- [Rolls-Royce RB211524G3T19](https://openairdocs.org/engine/rolls-royce-rb211524g3t19): 0 aircraft (registry code 54123)
- [Rolls-Royce RB211524H2T19](https://openairdocs.org/engine/rolls-royce-rb211524h2t19): 0 aircraft (registry code 54127)

## STCs approved under this data sheet (1)

- [STC SE00409LA](https://openairdocs.org/stc/SE00409LA): Installation of gas generator fairing thermal insulation blankets.. Air New Zealand Limited

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