# TCDS E12EU: Rolls-Royce Deutschland Ltd & Co KG - Type: Type certificate data sheet - Status: Current - Holder: Rolls-Royce Deutschland Ltd & Co KG - Revision: 26 - Revised: April 25, 2019 - Product: Engine - Certification basis: Part 21, Part 33 - Registered aircraft: 62, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/62/c6/62c681707f5c13cd77af6406db361c88612d5f8a94196613c0a96669b60dd804 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/88EB743D4A6075038625847E005DCD4B.0001 - Page: https://openairdocs.org/tcds/E12EU ## Models (22) As the data sheet lists them. - RB211-524B3-02 - RB211-524C2-B-19 - RB211-524B2-19 - RB211-524B-02 - RB211-524B-B-02 - RB211-524D4-19 - RB211-524D4X-19 - RB211-22B-02 - RB211-535C-37 - RB211-524C2-19 - RB211-535E4-B-75 - RB211-524D4-B-19 - RB211-524B4-02 - RB211-535E4-37 - RB211-22B-02 (MOD 72-8700) - RB211-524D4-B-39 - RB211-524D4X-B-19 - RB211-524D4-39 - RB211-524B2-B-19 - RB211-524B4-D-02 - RB211-535E4-B-37 - RB211-535E4-C-37 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text * PAGE 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 REV. 26 23 23 23 25 24 23 23 23 23 23 23 23 23 26 24 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E12EU TCDS NUMBER E12EU REVISION: 26 DATE: April 25, 2019 ROLLS-ROYCE, Deutschland Ltd. & Co. KG MODELS: RB211-22B-02 RB211-524D4-19 RB211-22B-02 (MOD 72-8700) RB211-524D4-39 RB211-524D4-B-19 RB211-524D4-B-39 RB211-524D4X-19 RB211-524D4X-B-19 RB211-524B-02 RB211-524B-B-02 RB211-535C-37 RB211-524B2-19 RB211-524B2-B-19 RB211-535E4-37 RB211-524B3-02 RB211-535E4-B-37 RB211-524B4-02 RB211-535E4-B-75 RB211-524B4-D-02 RB211-535E4-C-37 RB211-524C2-19 RB211-524C2-B-19 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E12EU) 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, German TYPE CERTIFICATE (TC) RECORD: Rolls-Royce, plc transferred to TC E12EU Rolls-Royce, Deutschland on February 21, 2019 TYPE (For all models) High bypass turbofan, three shaft. Single-stage low pressure fan driven by three-stage turbine. Seven-stage intermediate pressure compressor (see exceptions noted immediately below) driven by single stage turbine. Six-stage high pressure compressor driven by single stage turbine. Annular combustion chamber. Exceptions: Models RB211-535C, -535E4, -535E4-B, and -535E4-C have a six-stage intermediate pressure compressor. I. MODELS (See NOTES 1, 2, 5, and 10, For Models RB211- 22C & RB211-524-02, see NOTE 15) RB211-22B-02 RB211-22B- 02 (MOD 72- 8700) RB211-524B- 02, 524B-B- 02 RB211-524B3- 02, 524B4- 02, 524B4-D-02 RATINGS Maximum continuous thrust pounds At sea level static 40,140 ISA+9o to 25,000 ft or to 26,000 ft at Mach numbers 0.5 to 0.6 ISA+13o above - - 44,780 ISA+9o to 25,000 ft ISA+10o above - - - - Takeoff (5 minutes) thrust pounds At sea level static 41,030 ISA+13.9o 42,670 (1) - - 49,120 - - 49,120 (2) - - TCDS E12EU PAGE 2 1. ISA+8.4oC up to 5,600 feet, reducing linearly to 41,030 thrust pounds at ISA+13.9oC and 10,000 feet 2. RB211-524B4-D-02 only: 49,120 thrust pounds at ISA+17.8 oC up to 5,000 feet. I. MODELS (Continued) (See NOTES 1, 2, 5, and 10, For Models RB211- 22C & RB211-524-02, see NOTE 15) RB211-524B2 -19, 524B2- B -19 RB211- 524C2-19, 524C2-B-19 RATINGS Maximum continuous thrust pounds At sea level static 44,780 ISA+9o to 25,000 ft ISA+10o above 46,120 - - Takeoff (5 minutes) thrust pounds At sea level static 49,120 ISA+13.9o 50,600 - - II. MODELS (See NOTES 1, 2, 5, and 10, For Models RB211- 22C & RB211-524-02, see NOTE 15) RB211-524D4-19, 524D4-39, 524D4-B-19, 524D4-B-39 RB211- 524D4X-19, 524D4X-B-19 RB211-535C- 37 RB211-535E4- 37 RATINGS Maximum continuous thrust pounds At sea level static 47,320 ISA+10oC - - 33,500 - - 35,205 - - Takeoff (5 minutes) thrust pounds At sea level static (See Note 24) 51,980 (3) ISA+15o 52,810 (3) - - 36,720 (4) 39,610 (5) 3. RB211-524D4-19, -524D4-B-19, -524D4X-19, -524D4X-B-19 only: 53,460 thrust lbs. up to 2,000 ft., ISA+11.2 oC 4. ISA+13.9o up to 3,400 ft., and between 10,000 ft. and 15,000 ft. ISA+17.2o between 5,000 ft. and 9.000 ft. with linear variations between 3,400 ft. and 5,000 ft and 9,000 ft. and 10,000 ft. 5. ISA+13.9o up to 10,000 ft. ISA+20o between 12,500 ft. and 15,000 ft. with linear variations between 10,000 ft. and 12,500 ft. II. MODELS (Continued) (See NOTES 1, 2, 5, and 10, For Models RB211- 22C & RB211-524-02, see NOTE 15) RB211-535E4-B- 37, 535E4-B-75 RB211- 535E4-C-37 RATINGS Maximum continuous thrust pounds At sea level static 35,205 ISA+10oC 35,205 ISA +10ºC Takeoff (5 minutes) thrust pounds At sea level static (See Note 24) 42,540 (6) 42,540 (7) 6. RB211-535E4-B-37/-535E4-B-75: ISA+10o at sea level, linear variation between ISA+10oC and ISA+13.9oC between sea level and 4,000 ft, ISA +13.9º C between 4,000ft and 10,000ft, linear variation between ISA +13.9ºC and 20ºC between 10,000ft and 12,500ft. 7. ISA +12.5ºC at sea level, linear variation between ISA +12.5ºC and ISA +16.2ºC between sea level and 420ft, ISA + 16.2ºC between 420ft and 820ft, linear variation between ISA +16.2ºC and ISA +12.9ºC between 820ft and 1,200ft, linear variation between ISA +12.9ºC and ISA +13.9ºC between 1,200ft and 4,000ft, ISA +13. 9ºC between 4,000ft and 10,000ft, linear variation between ISA +13.9º C and ISA +20ºC between 10,000ft and 12,500ft, ISA +20º C between 12,500ft and 15,000ft. TCDS E12EU PAGE 3 MODELS / Group 1 RB211-22B- 02, 22B-02 (MOD 72- 8700) RB211- 524B-02, 524B-B- 02 RB211- 524B3-02 RB211- 524B4- 02, 524B4- D-02 RB211- 524B2- 19, 524B2- B-19 RB211- 524C2-19, 524C2-B- 19 FUEL (see NOTE 7) Fuel control Lucas type Woodward type Fuel pump Lucas type FFR 101 --- PAC 101 FFR 103 --- PAC 102 FFR 104 --- - - - - --- - - FFR 102 --- - - - - --- - - OIL (see NOTE 11) Tank capacity (U.S. pints nominal Usable oil (U.S. pints minimum) (includes altitude effects) 51.0 39.0 45.6 33.0 - - - - - - - - 57.3 47.5 - - - - IGNITION SYSTEM Two igniter units Rotax type Simmonds type Two igniter plugs Auburn type Champion type NB10605 --- YA 211-19 CH34157B - - --- - - - - - - --- - - - - - - --- - - - - - - --- - - - - - - --- - - - - PRINCIPLE DIMENSIONS, in. Length Front of nose to end of jet pipe nozzle Width Maximum over fan casing Height From lowest point on gearbox to top face of engine mounting pad Center of Gravity Aft of engine front suspen- sion center line 204.33 96.0 105.8 31.4 179.0 95.0 107.6 30.2 189.2 - - - - 30.5 - - - - - - 31.2 180.4 - - - - 30.2 - - - - - - 30.3 WEIGHT, lbs. 10,326 10,154 11,000 11,148 11,154 11,199 NOTES 1-16 1-15 - - - - 1-14, 16, 22 1-14, 22 TCDS E12EU PAGE 4 MODELS / Group 2 RB211- 524D4-19, 524D4-B-19, 524D4-39, 524D4-B-39 RB211- 524D4X- 19, 524D4X- B-19 RB211- 535C-37 RB211- 535E4-37 RB211-535E4- B-37, 535E4-B- 75, 535E4-C-37 FUEL (see NOTE 7) Fuel control Lucas type Woodward type Fuel pump Lucas type FFR 105 --- PAC 102 - - --- - - --- 8062-701 LP BPU 200 --- 8062-514 - - --- 8062-540(E4-B only) 8062-553 (C-37 only), - - OIL (see NOTE 11) Tank capacity (U.S. pints nominal Usable oil (U.S. pints minimum) (includes altitude effects) 57.3 47.5 - - - - 40.8 40.6 - - 38.4 - - - - IGNITION SYSTEM Two igniter units Rotax type Simmonds type Unison type Two igniter plugs Auburn type Champion type NB10605 --- --- YA 211-19 CH34157B - - --- --- - - - - --- 49.731 --- - - - - --- - - --- - - --- --- - -(E4-B only) 430152(C-37 only,) - -(E4-B only) CH34743(C-37 only) PRINCIPLE DIMENSIONS, in. Length Front of nose to end of jet pipe nozzle Width Maximum over fan casing Height From lowest point on gearbox to top face of engine mounting pad Center of Gravity Aft of engine front suspen- sion center line 189.8 95.0 107.6 31.1 - - - - - - - - 180.1 87.25 95.0 29.5 198.2 89.6 95.1 28.7 - - - - - - - - WEIGHT, lbs. 11.195 - - 7,680 7,603 - - NOTES 1-14, 22 - - 1-14, 17-21 - - - - TCDS E12EU PAGE 5 CERTIFICATION BASIS (All models except RB211-535E4-C-37) FAR 21.29 and FAR 33, effective February 1, 1965, as amended by FAR 33-1 through 33-3 and Special Condition No. 33-39-EU-9. Pursuant to FAR 21.29(a) (ii), Type Certificate E12EU was applied for on June 5, 1969 and issued on February 25, 1972, in validation of the British Air Registration Board’s certification of compliance with Special Condition No. 33-39-EU-9 and BCAR standards, which were found to provide a level of safety equivalent to the above FAR 33 regulations as follows: BCAR Section C. Issue 6, dated June 15, 1966, plus Blue Papers 415, 435, 436, 464, 468, 474, 476, 480, 481, 482, 499, 506, 544, 551 (Paragraph 3.2.2. only), and 554. (RB211-535E4-C-37) FAR 21.29 and FAR 33, effective February 1, 1965, as amended by FAR 33- 1 through 33-3, FAR 33.73 Amendment 4, FAR 33.17 Amendment 6, FAR 33.75 Amendment 6, and FAR 34, effective September 10,1990, as amended by FAR 34-1 through 34-3. The United Kingdom Civil Aviation Authority originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E12EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight 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 conforms to the type design approved under the U.S. Type Certificate E12EU, is in a condition for safe operation and has undergone a final operational check. To be considered eligible for installation on U.S. registered aircraft, each engine to be exported to the United States must comply with the following Rolls-Royce service bulletins, approved by the United Kingdom Civil Aviation Authority as Airworthiness Directives: Service Bulletin UK CAA AD Number UK CAA AD Approval Date RB.211-73-5184 CAA AD 019-03-81 February 20, 1981 RB.211-72-A6820 CAA AD 006-05-82 March 31, 1982 RB.211-72-5201 CAA AD 0037 PRE 80 May 11, 1982 RB.211-73-4305 CAA AD 0030 PRE 80 September 19, 1984 RB.211-73-3673 CAA AD 0025 PRE 80 September 19, 1984 RB.211-71-7383 CAA AD 010-05-84 August 30, 1988 RB.211-71-9270 CAA AD 014-03-90 March 6, 1990 RB.211-78-9274 CAA AD 019-10-90 September 3, 1990 RB.211-71-9546 CAA AD 003-07-92 April 30, 1992 RB.211-72-8963 CAA AD 010-01-90 February 20, 1997 RB.211-78-9574 CAA AD 007-06-92 July 12, 2001 RB.211-71-9276 CAA AD 002-07-92 July 12, 2001 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 E12EU PAGE 6 NOTES NOTE 1. ROTOR SPEED LIMITATIONS / PERCENT (See Note 24) LOW PRESSURE ROTOR (N1) MODELS: RB211- N1 100%= rpm Takeoff 5 minutes Maximum Continuous Maximum for Reverse Thrust per./sec. Transient 20 seconds Ground Idle(*) Min/Max 22B-02 22B-02 (MOD 72-8700) 524B-02 524B-B-02 524B3-02 524B4-02 524B4-D-02 524B2-19 524B2-B-19 524C2-19 524C2-B-19 524D4-19 524D4-B-19 524D4-39 524D4-B-39 524D4X-19 524D4X-B-19 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 3,900 rpm 99.5 - - 103.0 - - - - - - - - - - - - 104.0 - - 104.4 - - - - - - - - - - 101.0 - - 103.0 - - - - - - - - - - - - 103.0 - - 103.7 - - - - - - - - - - 101.3/30 - - 90.0/60 - - - - - - - - - - - - - - - - - - - - - - - - - - - - 103.0 - - 104.0 - - - - - - - - - - - - 105.0 - - 106.0 - - - - - - - - - - 21.0/23.3 - - 22.5/23.5 - - - - - - - - 22.0/23.5 - - - - - - 22.6/24.1 - - - - - - - - - - MODELS: RB211- N1 100%= rpm Takeoff 5 minutes Maximum Continuous Maximum for Reverse Thrust per./sec. Transient 20 seconds Ground Idle(*) Min/Max 535C-37 535E4-37 535E4-B-37 535E4-B-75 535E4-C-37 4,500 rpm 4,500 rpm 4,500 rpm - - - - 110.0 108.8 - - - - - - 108.5 108.4 - - - - - - 100.0/60 84.3/40 - - - - - - 111.0 110.0 - - - - - - See NOTE 19 - - - - - - - - (*) Ground idle varies with O.A.T; see Rolls-Royce Operating Instructions INTERMEDIATE PRESSURE ROTOR (N2) 100% N2 = 7,000 rpm HIGH PRESSURE ROTOR (N3) 100% N3 = 10,611 rpm MODELS: RB211- Takeoff 5 minutes Maximum Continuous Transient 20 seconds Takeoff 5 minutes Maximum Continuou s Maximum Continuous (MOD 5089) Transient 20 seconds 22B-02 22B-02 (MOD 72-8700) 524B-02 524B-B-02 524B3-02 524B4-02 524B4-D-02 524B2-19 524B2-B-19 524C2-19 524C2-B-19 102.5 - - 106.0 - - - - 107.0 106.0 - - - - - - - - 101.5 - - 102.0 104.0 102.0 103.5 102.0 102.0 104.0 102.5 104.0 106.0 - - 107.0 - - - - 108.0 107.0 - - - - - - - - 95.0 - - 97.0 98.3 97.0 97.5 97.0 96.5 98.4 97.1 98.6 93.7 - - 94.5 96.3 94.5 95.3 94.5 93.7 96.3 94.4 96.3 94.2 --- --- --- --- --- --- --- --- --- --- 96.2 - - 98.3 99.3 98.3 98.5 98.3 98.3 99.4 98.3 99.6 TCDS E12EU PAGE 7 524D4-19 524D4-B-19 524D4-39 524D4-B-39 - - - - - - - - 103.0 - - - - - - - - - - - - - - 97.5 98.6 97.5 98.0 95.2 96.5 95.2 95.7 --- --- --- --- 98.9 99.6 98.9 99.0 524D4X-19 524D4X-B-19 535C-37 535E4-37 535E4-B-37 535E4-B-75 535E4-C-37 535E4-C-37-37(with SB RB.211-73-D716) - - - - 101.9 100.3 - - - - 100.7 101.7 - - - - 99.3 98.0 - - - - - - - - - - - - 102.9 101.3 - - - - 102.3 103.3 97.5 98.6 94.6 99.0 - - - - - - 99.7 95.2 96.5 93.0 95.8 - - - - - - - - --- --- --- --- --- --- --- - - 98.9 99.6 95.6 100.2 - - - - - - 101.5 NOTE 2. TEMPERATURE LIMITATIONS / DEGREES CENTIGRADE (See Note 24) TURBINE GAS TEMPERATURES Indicated temperatures measured at the low pressure NGV when fitted with the approved ballast resistor specified in the applicable engine manual. MODELS: RB211- Maximum for Acceleration Takeoff 2 min. (*) Maximum For Takeoff 5 min. (*) Maximum Continuous Maximum Continuous (mod 5089) Maximum Over- Temperature 20 secs. Starting on Ground Starting in Flight Ground Idle 22B-02 22B-02 (MOD 72-8700) 524B-02 524B-B-02 524B3-02 524B4-02 524B4-D-02 524B2-19 524B2-B-19 524C2-19 524C2-B-19 524D4-19 524D4-B-19 524D4-39 524D4-B-39 524D4X-19 524D4X-B-19 535C-37 535E4-37 535E4-B-37 535E4-B-75 535E4-C-37 738 - - --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- 728 - - 785 - - - - - - - - - - - - - - - - - - - - - - - - - - - - 850 - - 877 - - - - 700 - - 732 - - - - - - - - - - - - - - - - 722 722 722 722 722 722 795 - - - - - - - - 710 --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- 750 - - 800 - - - - - - - - - - - - - - - - - - - - - - - - - - - - 870 - - 897 - - - - 550 - - 600 - - - - - - - - - - - - - - - - - - - - - - - - - - - - 570 - - - - - - - - 550 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 570 - - - - - - - - 460 - - --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- (*) Total combined time period for acceleration takeoff and takeoff not to exceed 5 minutes TCDS E12EU PAGE 8 Note 2. (Continued) FUEL TEMPERATURES See NOTE 13 Measured at fuel filter outlet OIL TEMPERATURES TURBINE COOLING AIR TEMPERATURE Models: RB211- Maximum for Continuous Operation Maximum Transient 15 min. max. Maximum Unrestricted Maximum Transient 15 min. Maximum 22B-02 22B-02 (MOD 72-8700) 524B-02 524B-B-02 524B3-02 524B4-02 524B4-D-02 524B2-19 524B2-B-19 524C2-19 524C2-B-19 524D4-19 524D4-B-19 524D4-39 95 - - - - - - - - - - - - - - - - - - - - - - - - - - 115 - - - - - - - - - - - - - - - - - - - - - - - - - - 100 (1) - - 170 (2) - - - - 160 - - 170 - - - - - - 167 - - - - 600 - - - - - - - - - - - - - - - - - - - - - - - - - - 524D4-B-39 524D4X-19 524D4X-B-19 535C-37 535E4-37 535E4-B-37 535E4-B-75 535E4-C-37 - - - - - - 49(3) - - - - - - - - - - - - - - --- --- --- --- - - - - - - - - 160 170 177 - - - - --- --- --- --- --- --- --- - - - - - - - - - - - - - - - - - - (1) HP filter outlet (2) Combined scavenge (3) LP pump inlet NOTE 3. FUEL AND OIL PRESSURE LIMITATIONS (psig) FUEL PRESSURE OIL PRESSURE Models: RB211- Minimum (1) Maximum (2) Normal between ground/low idle and 70% N3 Normal above 70% N3 Minimum, between ground/low idle and 70%N3 Minimum above 70% N3 Transient Minimum 5-min. limit 22B-02 22B-02 (MOD 72- 8700) 524B-02 524B-B-02 524B3-02 524B4-02 524B4-D-02 524B2-19 524B2-B-19 5 - - - - - - - - - - - - - - - - 50 - - - - - - - - - - - - 55 - - 35 to 100 - - - - - - - - - - - - - - - - 40 to 100 - - - - - - - - - - - - - - - - 35 - - 25 - - - - - - - - - - - - 35 - - - - - - - - - - - - - - - - 18 - - - - - - - - - - - - - - - - TCDS E12EU PAGE 9 Note 3. (Continued) FUEL AND OIL PRESSURE LIMITATIONS (psig) Models: RB211- FUEL PRESSURE OIL PRESSURE Minimum( 1) Maximum (2) Normal between ground/low idle and 70% N3 Normal above 70% N3 Minimum, between ground/low idle and 70%N3 Minimum above 70% N3 Transient Minimum 5-min. limit 524C2-19 524C2-B-19 524D4-19 524D4-B-19 524D4-39 524D4-B-39 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 524D4X-19 524D4X-B-19 535C-37 535E4-37 535E4-B-37 535E4-B-75 535E4-C-37 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 25 to 100 - - - - - - - - - - - - 35 to 100 - - - - - - - - - - - - 18 at 50% N3 to 25 at 70% N3 - - - - - - - - - - - - 25 at 70% N3 to 35 at 93%N3 or greater - - - - - - - - - - - - --- --- --- --- --- 1. Minimum (measured at inlet to LP fuel pump) plus true fuel vapor pressure with vapor/liquid ratio of zero between sea level and 45,000 feet. 2. Maximum (measured at inlet to LP fuel pump) NOTE 4. (A) BLEED AIR AND (B) POWER EXTRACTION LIMITATIONS FOR MODELS RB211- (A) Maximum Bleed (percent of gas generator compressor flow) for aircraft services. 22B-02 22B-02 (MOD 72-8700) 524B-02 524B-B-02 524B3-02 524B4-02 524B4-D-02 (1) HP bleed From ground idle to changeover point, 9 percent for normal operation and 12 percent in the event of temporary unbalanced system operation or after an engine or system failure which eliminates bleed flow from the affected engine. Above the changeover point, zero. (2) IP Bleed For normal operation from ground idle to changeover, 1.5 percent; and from changeover to takeoff, 6.5 percent. In the event of temporary unbalanced system operation or after an engine or system failure, 6.5 percent from ground idle to takeoff. HP/IP changeover point is controlled by a switching valve and varies linearly with ambient pressure from 39.5+3 psig IP compressor delivery pressure (P3) at sea level to 22+1.5 psig (P3) at 35,000 feet altitude, with straight line variation above and below 35,000 feet. Bleed air for nose cowl anti-icing, which is approximately 1.5 percent compressor flow, is taken from the IP port and is included in the maximum bleed flow values quoted for IP bleed. TCDS E12EU PAGE 10 NOTE 4. (Continued) FOR MODELS RB211- (A) Maximum Bleed (percent of gas generator compressor flow) for aircraft services. 524B2-19 524B2-B-19 524C2-19 524C2-B-19 524D4-19 524D4-B-19 524D4-39 524D4-B-39 524D4X-19 524D4X-B-19 The engine bleed is automatically scheduled from the engine IP and HP ports by a switching valve which selects from the appropriate port. With switching valve 60B40123-2, bleed air is extracted from the IP delivery port at engine power settings above that giving P4 (HP compressor delivery pressure) greater than 84±3 psig at sea level and 84+4 psig at 30,000 feet altitude, then decreasing linearly with ambient pressure 71±3 psig at 45,000 feet. With switching valve 60B40123-3, bleed air is extracted from the IP delivery port at engine power settings above that giving, at maximum setting, a P4 greater than 89 psig between sea level and 36,000 feet, decreasing linearly to 66 psig at 45,000 feet, and, at minimum setting, 79 psig between sea level and 30,000 feet, decreasing linearly to 56 psig at 45,000 feet. Bleed air for nose cowl anti-icing, which is approximately 1.5 percent compressor flow, is taken from whichever bleed port is supplying air for aircraft service and is included in the maximum flows quoted below: (1) HP bleed: From ground idle to changeover point: 9.0 percent (2) IP bleed: Decrease linearly with increase of HP compressor delivery pressure so that bleed is: At the changeover point: 7.2 percent At maximum continuous condition: 5.0 percent At maximum takeoff conditions: 3.4 percent (3) LP bleed (percent fan flow) From ground idle to 93 percent N3 RPM: 0.5 percent At maximum continuous: 0.4 percent From maximum continuous to maximum takeoff: 0.6 percent FOR MODELS RB211- (A) Maximum Bleed (percent of gas generator compressor flow) for aircraft services. 535C-37 535E4-37 535E4-B-37 535E4-B-75 535E4-C-37 The engine bleed is automatically scheduled from the HP2 and HP6 bleed ports by a switching valve which selects from the appropriate port. The switching valve settings are: HP Compressor Delivery Pressure (P4) Sea Level to 31,000 Ft. Above 31,000 Ft. 535C-37: 94 psig 75 psig 535E4-37: 107 psig 91 psig 535E4-B-37: 107 psig 91 psig 535E4-B-75 107 psig 91 psig 535E4-C-37 107 psig 91 psig Bleed air for nose cowl anti-icing (approximately 1.5 percent compressor flow) is taken from the HP2 port and is included in the maximum bleed flow values quoted for HP2 bleed. (1) HP6 Bleed Normal Operation Failure Conditions 535C-37: 4.0 percent 10.0 percent 535E4-37: 5.5 percent 9.4 percent 535E4-B-37: 5.5 percent 9.4 percent 535E4-B-75: 5.5 percent 9.4 percent 535E4-C-37 5.5 percent 9.4 percent TCDS E12EU PAGE 11 NOTE 4. (Continued) FOR MODELS RB211- (Cont) (A) Maximum Bleed (percent of gas generator compressor flow) for aircraft services. 535C-37 535E4-37 535E4-B-37 535E4-B-75 535E4-C-37 (2) HP2 Bleed Normal Operation Low Idle to Changeover Point to Maximum Continuous Changeover Point Maximum Continuous To Takeoff 535C-37: 1.5 percent 4.0 percent 2.0 percent 535E4-37: 2.3 percent 4.8 percent 2.0 percent 535E4-B-37: 2.3 percent 4.8 percent 2.0 percent 535E4-B-75: 2.3 percent 4.8 percent 2.0 percent 535E4-C-37 2.3 percent 4.8 percent 2.0 percent Failure Conditions 535C-37: 2.3 percent 7.6 percent 2.4 percent 535E4-37: 2.3 percent 7.7 percent* 2.5 percent 535E4-B-37: 2.3 percent 7.7 percent* 2.5 percent 535E4-B-75: 2.3 percent 7.7 percent* 2.5 percent 535E4-C-37 2.3 percent 7.7 percent* 2.5 percent (3) LP Bleed (percent fan flow): For both normal and failure conditions LP bleed is 1.0 percent between low idle and takeoff. *5.4 percent at maximum continuous FOR MODEL SERIES (B) SHAFT POWER EXTRACTION LIMITATIONS Accessory drive provision (continuous power as listed may be extracted under all engine operating conditions) RB211-22B- Torque (lb-in) RB211-524- Drive Rotation Speed Ratio to HP Rotor Speed Continuous Maximum Instantaneous Overhang (in-lb) Starter IDG Tachometer (HP) CCW CCW CW 1.0036 0.8524 0.3958 15,300 (190 HP) 7 19,320 950 HP 5 secs 50 800 1,750 --- Hydraulic Pump (For each of two drives) CCW 0.3842 1,450 7,250 400 CW = Clockwise CCW = Counterclockwise FOR MODEL SERIES (B) SHAFT POWER EXTRACTION LIMITATIONS Accessory drive provision (continuous power as listed may be extracted under all engine operating conditions). RB211-535- Torque (lb-in) Drive Rotation Speed Ratio to HP Rotor Speed Continuous Maximum Instantaneous Overhang (in-lb) IDG Tachometer (HP) CCW CCW 0.8660 0.3953 (175 HP) 7 450 HP 5 secs 50 1,750 --- RB211-535E4- B-75 Hydraulic Pump (For each of two drives) CCW - - 0.3677 - - 1,300 1,600 --- --- 400 --- Speed Ratio to MaxTorque (lb-in)at and above 1,700 Drive Rotation HP Rotor Speed Static Overhang (in-lb) Transient Starter RPM Starter CCW 0.9942 8,160 800 16,320 6,120 CW = Clockwise CCW = Counterclockwise TCDS E12EU PAGE 12 NOTE 5. The ratings are based on static test stand operation under Conditio ns A and B which follow. FOR ALL MODELS: CONDITION 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 (4) Turbine temperature and engine rotor ratings not exceeded Condition B Equivalent Bare Engine Thrust (1) Exhaust Nozzle Configuration (2) For Models RB211 Takeoff (lb) Maximum Continuous (lb) T/R Simulator Fan Nozzle Jet Pipe 22B-02 22B-02 (MOD 72- 8700) 524B-02 524B-B-02 524B3-02 524B4-02 524B4-D-02 524B2-19 524B2-B-19 524C2-19 524C2-B-19 524D4-19 524D4-B-19 524D4-39 524D4-B-39 524D4X-19 524D4X-B-19 535C-37 535E4-37 535E4-B-37 535E4-B-75 535E4-C-37 42,000 43,680 50,000 - - - - - - - - - - - - 51,500 - - 53,000(3) 53,000(3) 53,000 - - 53,835(3) 53,835(3) 37,400 40,100 43,100 - - - - 41,130 41,130 45,625 - - - - - - - - - - - - 47,000 - - 48,160 48,160 48,160 - - 48,160 48,160 34,150 35,640 35,640 - - - - ATF Sch 4809/TR 502 - - ATF Sch 4809/TR 514 - - ATF Sch 4809/TR 512 - - - - - - - - - - - - TR 525 - - - - - - - - - - TR 551 TR 552 - - - - TR 564 ATF Sch 4808 - - LJ 28,580 - - LJ 27,530 - - - - - - - - - - - - --- --- --- --- --- --- --- --- --- --- --- ATF 475/JP 505 - - LJ 30,982/JP 515 - - - - - - - - LJ 30,920/JP 512 - - - - - - LJ 31,118/JP518 - - - - - - - - - - JP 551 JP 552 - - - - - - (1) The equivalent bare engine thrust (lbs) is rated thrust, exclusive of propulsion fan duct and thrust reverser, jet pipe, and portion of the pylon washed by the fan stream. (2) Includes one configuration each of the three items or an approved equivalent to the same aerodynamic configuration (3) 54,500 lbs equivalent thrust for reduced envelope takeoff NOTE 6. For the RB211-535E4-37, -535E4-B-37, -535E4-B-75 and -535E4-C-37 models, power setting, power check, and control of the engine output are to be based on Rolls-Royce engine charts included in relevant Operating Instructions (listed in Note 10) regarding Integrated Engine Pressure Ratio (IEPR) or Engine Pressure Ratio (EPR). Pressure probes are included in the engine for this purpose. NOTE 7. Approved fuels and fuel additives are listed in relevant Operating Instructions as listed in Note 10. TCDS E12EU PAGE 13 NOTE 8. Life limited parts are identified in relevant Time Limits Manuals as follows: T-211 (22B) - 1RR RB211-22B's T-211 (524) - 2RR RB211-524B2, C2, and D4 Series T-211 (524) - 3RR RB211-524B, B3, and B4 Series T-211 (535) - 4RR RB211-535E4-B-75 T-211 (535) - 5RR RB211-535C-37 T-211 (535) - 6RR RB211-535E4, E4-B-37, E4-C-37 NOTE 9. This engine approval includes the bare engine plus thrust reverser, engine mounting feet and links, core engine cowlings, engine accessories, coolers, filters, harness, and instrumentation transmitters as defined in Lists 3 and 5 of the Rolls-Royce Drawing Introduction Sheet (DIS) as listed in Note 10. NOTE 10. RB211 series Manuals and Drawing Introduction Sheets (DIS) approved under BCAR requirements and accepted as equivalent to FAR 33.5 requirements Exhaust Nozzle Configuration For Models RB211 Introduction Sheet (DIS) Operating Instructions Maintenance Manual Installation Manual Engine Thrust Reverser 22B-02 22B-02 (MOD 72-8700) 524B-02 524B-B-02 524B3-02 524B4-02 524B4-D-02 524B2-19 524B2-B-19 524C2-19 524C2-B-19 524D4-19 524D4-B-19 524D4-39 524D4-B-39 524D4X-19 524D4X-B-19 535C-37 535E4-37 535E4-B-37 535E4-B-75 535E4-C-37 1004 1004 1068 2079 1088 1089 (2) 2077 (2) 1071 (2) 2068 1093 (2) 2069 1091 (2) 2070 2028 (2) 2028 (2) 2107 2108 1094 (4) 2015 (2) 2106 (2) 2142 2224(2) F-RB211-T - - F-211(524)-T - - - - - - - - F-211(525)-BSP(3) - - F-211(524)-B - - F-211(524)-BSP(3) - - - - - - - - - - F-211(535)-B F-211(535E4)-B - - F-211(535)-Tu F-211(535E4)-B M-211-TRR - - M-211(524)-T - - - - - - - - M-211(524)-B - - M-211(524)-B - - M-211(524)-B - - - - - - - - - - M211(535)-B - - - - M211(535)-Tu D633N193(5) EL2605(1) - - EL2805 Part A - - - - - - - - EL 2806 - - EL 2806 - - EL 2806 - - - - - - - - - - EL 2811A - - - - MISC 2717 EL2811A 0-211En-TRR - - - - - - - - - - B0-211En(524)-T/B - - 0-211En(524)-T/B - - 0-211En(524)-T/ - - - - - - - - - - E-211(535)-BRR E-211(535E)-6RR - - E-211(535)-4RR E-211(535)-6RR 0-211Tr-TRR - - - - - - - - - - B0-211TR(524)T/B - - 0-211TR(524)-T/B - - 0-211TR(524)LW- - - - - - - - - - - E-211(535)-BRR E-211(535E)-6RR - - E-211(535)-4RR E-211(535)-6RR (1) Part A, Addendum 1 (2) Includes the engine starter (3) Both F-211(524)-BSP and F-211(524)-B apply to this model (4) For the RB211-535C-37, the build standard for FAA approval is defined by Quick Engine Change (QEC) Number UL10055 or UL20056, or subsequently approved alterntives. These parts lists specify the heated, metallic spinner. (5) Boeing 757 Aircraft Maintenance Manual TCDS E12EU PAGE 14 NOTE 11. Approved oils are listed in the relevant Rolls-Royce Operating Instructions (Note 10). Also, oils of the approved types when reclaimed to approved Rolls-Royce standards for the appropriate viscosity grade are approved for use. NOTE 12. These engines comply with the applicable exhaust emissions and fuel venting requirements of SFAR 27-5 and 40CRF 87.7(b) under exemption 3914 January 25, 1984. NOTE 13. Although acceptable, it is not mandatory that individual engine instruments and red line markings be provided for these fuel temperature limitations, provided that the installer can prove to the aircraft certification authority that these limits are not likely to be exceeded within the approved aircraft operating envelope under reasonably probable fault conditions for each proposed installation. NOTE 14. MODEL CHARACTERISTICS OF THE RB-211 ENGINE SERIES The -22C-02 is the basic model installed in the Lockheed Tristar aircraft. The -22C was added May 23, 1972 and deleted on 04/22/2019. (see NOTE 15). The - 22B-02 is an improved performance variant of the -22C-02 with higher limits and maximum continuous thrust. The -22B-02 was added April 4, 1973. The -524 series of engines are growth versions of the -22B with increased takeoff and maximum continuous ratings achieved by approved temperature capability and efficiency of the HP and IP turbine components and by increased airflow of the core engine. The -524-02 engine is fitted in the Lockheed Tristar aircraft (NOTE 15). The -524-02 and -524B-19 were added on March 24, 1976, and the - 524B-19 engine was deleted on October 16, 1979 (NOTE 16). The -524-02 was deleted on March 22, 1989 (NOTE 16). The -524B2-19 and -524B2-39 engines incorporate improved performance margins and handling features and are installed in Boeing 747 aircraft. The -524B2-19 engine was added on December 6, 1977. The -524B2-39 engine was added on November 17, 1978. The -524B-02 engine is a derivative of the -524-02 engine with improved hot day thrust capability and is installed in the Lockheed Tristar aircraft. The -524B-02 engine was added on November 17, 1978. The -524B3-02 engine is a derivative of the -524B-02 engine with reduced weight and improved specific fuel consumption and is installed in the Lockheed Tristar aircraft. The -524B3-02 was added October 16, 1979. The -524C2-19 is an updated derivative of the -524B2-19 with an improved HP turbine cooling systems and is installed in the Boeing 747 aircraft. The -524C2-19 was added on April 25, 1980. The -524B4-02 engine is a derivative of the -524B3-02 engine with improved specific fuel consumption and is installed in Lockheed Tristar aircraft. The -524B4-02 engine was added on December 24, 1980. The -524D4-19 and -524D4-39 engines are updated derivatives of the -524C2-19 engine with improved specific fuel consumption and are installed in Boeing 747 aircraft. The -524D4-19 engine was added on June 30, 1981. The - 524D4-39 engine was added September 26, 1983. The -535C-37 engine is a reduced thrust derivative of the -22B and -524 engines with a reduced diameter fan and is installed in the Boeing 757 aircraft. The -535C-37 was added on September 15, 1981. The -535E4-37 engine is an increased thrust and improved specific fuel consumption derivative of the -535C-37 and is installed in the Boeing 757 aircraft. The -535E4-37 engine was added on February 28, 1984. The -524D4-19 and -524D4-B-19 engines may be used at an increased takeoff thrust subject to flat rating specified, within the existing operating limitation. This variation was added on January 22, 1986. Note 14. (Continued) The -524B4-D-02 engine may be used at an extended maximum takeoff thrust flat rating specified. This variation was added on August 30, 1987. TCDS E12EU PAGE 15 The -524B-B-02, -524B2-B-19, -524C2-B019, -524D4-B-19, and -524D4-B-39 models are introduced by the incorporation of Rolls-Royce Modification SB 72-7730, which introduces an improved HP turbine assembly and necessitates a revision to HP and IP speed limitations. these variants were added on August 30, 1987. The -22B-02 (Mod 72-8700) is a re-rate of the existing -22B-02 model. The new rating increases takeoff performance at lower ambient conditions. This variant was added on June 6, 1988. The -524-D4X-19 and -524D4X-B-19 engines are mechanically identical to the -524D4-19 and - 524D4-B-19 respectively but features a 1.6 percent increase in maximum takeoff thrust over the whole takeoff envelope. These variants were added on March 22, 1989. The -535E4-B-37 engine is a derivative of the -535E4-37 with increased maximum takeoff thrust and is installed in the Boeing 757 aircraft. The -535E4-B-37 was added on March 22, 1989. The -535E4-B-75 engine is similar to the -535E4-B-37 but has installation features to suit the Tupplov TU204 Aircraft. The -535E4-B-75 was added on February 19, 1997. The -535E4-C-37 engine is similar to the -535E4-B-37, but it incorporates various modifications to permit a takeoff "bump" rating at a range of ambient conditions at an altitude of 620 ft. The -535E4- C-37 was added on June 22, 2001. NOTE 15. There are no -22C or -524-02 engine models in existence. The -22C was retained on this TCDS until April 25, 2019 when it was deleted based on its removal from the UK CAA TCDS as of December 1974 per EASA’s April 15, 2019 statement. Therefore, -22C and -524-02 rating limits are not shown. The -22C engines was flat rated to ISA+3.9 degrees at 41,030 pounds; i.e., bare engine equivalent 42,000 lbs. The -22C engine was converted to -22B standard by incorporation of Rolls-Royce Service Bulletin RB211-72-2500. The -524-02 engine was flat rated to ISA+13.9 degrees at 47,140 lbs. (bare engine thrust equivalent 48,0000 pounds). The - 524-02 engine was converted to -524B-02 standard by incorporation of Rolls-Royce Service Bulletin No. 5232. NOTE 16. These engine models are deleted: Some initial engines were identified as -22 with the same configuration as -22C but performance flat rated to different ambient air temperature. No engines now exist to -22 standard. They were deleted from this TCDS on May 13, 1974. The -22CA engine was full -22B mechanical standard operated at - 22C thrust levels as defined in Rolls-Royce Modification 3001. Some -22CA limits were different from -22B and -22C added April 4, 1973, and deleted on March 24, 1976. All - 22CA engines have been converted to -22B models. The -524B-19 engine model was deleted October 16, 1979. All -524B-19 engines have been converted to -524B2-19 engines. The -524B2-39 engine model was deleted on August 30, 1987, as none of these engines exist in service. The -524-02 engine model was deleted on March 22, 1989, as all such engines have been converted to the -524B-02 variant. NOTE 17. The -535C-37, -535E4-37, -535E4-B-37, -535E4-B-75, and -535E4-C-37 engines comply with FAR 33.77 as introduced by Amendment 33-6. NOTE 18. The introduction of SB 75-6556 on the -535C-37 incorporated the Deceleration Detection Unit (DDU) into the Bleed Control Valve Unit (BCVU) and hence provided the ability to functionally check the CCU with the Built-In Test Equipment (BITE) system. NOTE 19. The aircraft crew drill for ground starting the -535C-37, -535E4-37, -535E4-B-37, -535E4-B-75, and - 535E4-C-37 engines must include a statement that at stabilized low idle, LP rotor speed (N1) must not be below 22.5 percent for the -535C-37 and 19.8 percent for the - 535E4-37, -535E4-B-37, -535-E4-B-75 and -535E4-C-37. TCDS E12EU PAGE 16 NOTE 20. During flight in icing conditions, the -535C-37 engine may be operated satisfactorily at LP rotor speeds (N1) down to high idle and the -535E4-37, -535E4-B-37, -535E4-B-75 and -535E4-C-37 down to low idle. Minimum corresponding N1 at high idle for the -535C-37 is 33.5 percent and minimum corresponding low idle for the -535E4-37, -535E4-B-37, -535E4-B-75 and -535E4-C-37 is 29.5 percent. On the ground in icing conditions, the engines may be operated satisfactorily at LP rotor speeds down to low idle. Minimum corresponding N1 at low idle is 22.5 percent for the -535C-37 and 19.8 percent for the -535E4-37, -535E4-B-37, -535E4-B-75 and -535E4-C-37. NOTE 21. An optional feature of the -535C-37, -535E4-37, -535E4-B-37, -535E4-B-75 and -535E4-C-37 engine is a supervisory Electronic Engine Control system by which the trimming of fuel is applied through the prime hydromechancial fuel flow regulator. Electronic Engine Control software meets “critical” standard of RTCA DO-178. NOTE 22. During flight in icing conditions, the -524B2-19, -524B2-B-19, -524C2-19, -524C2-B-19, -524D4- 319, -524D4-B-19 and -524D4-B-39 engines may be operated satisfactorily at LP rotor speeds (N1) down to low idle. Minimum corresponding N1 at low idle for these engines is 22.0 percent. On the ground in icing conditions, the engines may be operated satisfactorily at LP rotor speeds down to low idle. Minimum corresponding N1 at low idle is 22.0 percent for the -524B2-19, -524B2-B-19, - 524C2-19, -524C2-B-19 and 22.6 percent for the - 524D4-19, -524D4-39, -524D4-B-19, -524D4-B- 39, -524D4X-19 and -524D4X-B-19. NOTE 23. 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. NOTE 24. For the RB211-535 models, the takeoff rating and its associated 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 (71, first 50, in force first) - [AD 2024-10-06](https://openairdocs.org/ad/2024-10-06): Engine (Turbine/Turboprop) · Rolls-Royce Deutschland RB211-535E4-37, RB211-535E4-B-37 and RB211-535E4-C-37. Effective Jun 27, 2024 - [AD 2023-18-05](https://openairdocs.org/ad/2023-18-05): Turbine Engine Compressor Section · Rolls-Royce Deutschland RB211-535C-37. Effective Oct 30, 2023 - [AD 2020-08-03](https://openairdocs.org/ad/2020-08-03): Turbine Engine Compressor Section · Rolls-Royce Deutschland RB211-535E4-37, RB211-535E4-B-37, RB211-535E4-B-75 and 1 more. Effective May 18, 2020 - [AD 2017-24-08](https://openairdocs.org/ad/2017-24-08): Fuel control/Turbine engines · Rolls-Royce RB211-535E4-37, RB211-535E4-B-37 and RB211-535E4-C-37. Effective Jan 16, 2018 - [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 2016-03-04](https://openairdocs.org/ad/2016-03-04): Life-limited rotating parts · Rolls-Royce RB211-535E4-37, RB211-535E4-B-37 and RB211-535E4-C-37. Effective Mar 15, 2016 - [AD 2015-16-03](https://openairdocs.org/ad/2015-16-03): High-pressure turbine (HPT) blades · Rolls-Royce RB211-524B-02, RB211-524B2-19, RB211-524B3-02 and 6 more. Effective Sep 15, 2015 - [AD 2015-07-01](https://openairdocs.org/ad/2015-07-01): Low-pressure turbine (LPT) stage 3 turbine blades · Rolls-Royce RB211-524B-02, RB211-524B-B-02, RB211-524B2-19 and 4 more. Effective May 8, 2015 - [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 2013-16-23](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 2012-02-11](https://openairdocs.org/ad/2012-02-11): LP turbine stage 1, 2, and 3 discs · Rolls-Royce RB211-535E4-37, RB211-535E4-B-37, RB211-535E4-B-75 and 1 more. Effective Mar 6, 2012 - [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 2010-17-10](https://openairdocs.org/ad/2010-17-10): Rear cooling air holes · Rolls-Royce RB211-22B-02, RB211-524B4-D-02, RB211-524D4-19 and 5 more. Effective Sep 27, 2010 - [AD 2010-17-13](https://openairdocs.org/ad/2010-17-13): LPT casings · Rolls-Royce RB211-524C2-19 and RB211-524C2-B-19. Effective Sep 22, 2010 - [AD 2009-20-14](https://openairdocs.org/ad/2009-20-14): Eddy current inspection (ECI) · Rolls-Royce RB211-535E4-37, RB211-535E4-B-37 and RB211-535E4-B-75. Effective Nov 17, 2009 - [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 2006-17-12](https://openairdocs.org/ad/2006-17-12): High pressure (HP) turbine discs · Rolls-Royce RB211-22B-02, RB211-535C-37, RB211-535E4-37 and 3 more. Effective Sep 27, 2006 - [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 2003-14-21](https://openairdocs.org/ad/2003-14-21): Engine turbine cooling air overheat monitoring panel · Lockheed Martin L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15 and 7 more. Effective Aug 25, 2003 - [AD 2003-13-12](https://openairdocs.org/ad/2003-13-12): Intermediate pressure (IP) compressor · Rolls-Royce RB211-22B-02 and RB211-22B/MOD 72-8700. Effective Aug 1, 2003 - [AD 2003-10-03 R1](https://openairdocs.org/ad/2003-10-03-R1): High pressure (HP) turbine discs · Rolls-Royce RB211-535E4-B-37 and RB211-535E4-B-75. Effective Jun 20, 2003 - [AD 2003-10-02](https://openairdocs.org/ad/2003-10-02): Low pressure (LP) compressor · Rolls-Royce RB211-524C2-19 and RB211-524C2-B-19. Effective Jun 19, 2003 - [AD 2001-19-05](https://openairdocs.org/ad/2001-19-05): High Speed Gearbox Drive · Rolls-Royce RB211-535C-37, RB211-535E4-37, RB211-535E4-B-37 and 1 more. Effective Oct 11, 2001 - [AD 2000-18-03](https://openairdocs.org/ad/2000-18-03): Cold Stream Nozzle Assembly · Rolls-Royce RB211-524D4-19, RB211-524D4-B-19, RB211-524D4-B-39 and 2 more. Effective Sep 22, 2000 - [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 2000-09-14](https://openairdocs.org/ad/2000-09-14): Radial Drive Steady Bearings · Rolls-Royce RB211-535C-37, RB211-535E4-37, RB211-535E4-B-37 and 1 more. Effective Jul 11, 2000 - [AD 97-02-12](https://openairdocs.org/ad/97-02-12): Fuel Flow Governor (FFG) · Rolls-Royce RB211-535E4-37, RB211-535E4-B-37 and RB211-535E4-B-75. Effective Apr 4, 1997 - [AD 95-04-02](https://openairdocs.org/ad/95-04-02): Nozzle Guide Vane Assembly · Rolls-Royce RB211-524B-02, RB211-524B-B-02, RB211-524B2-19 and 4 more. Effective May 8, 1995 - [AD 87-23-04 R1](https://openairdocs.org/ad/87-23-04-R1): Low PressureTurbine Disk · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524-02 and 7 more. Effective May 31, 1989 - [AD 87-25-04](https://openairdocs.org/ad/87-25-04): Fuel Quantity Indication System · Rolls-Royce RB211-535C-37, RB211-535E4-37, RB211-535E4-B-37 and 1 more. Effective Dec 8, 1987 - [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 86-20-09](https://openairdocs.org/ad/86-20-09): Intermediate Pressure Compressor (IPC) Stage 6 to 7 Rotor Assemblies · Rolls-Royce RB211-22B-02 and RB211-22B/MOD 72-8700. Effective Nov 4, 1986 - [AD 85-10-05 R1](https://openairdocs.org/ad/85-10-05-R1): Low Pressure Rotor Location Bearing Area Modifications · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700, RB211-524B-02 and 14 more. Effective Mar 28, 1986 - [AD 80-13-05 R1](https://openairdocs.org/ad/80-13-05-R1): (HPC) Rotor Stage 1 And 2 Disk Assembly · Rolls-Royce RB211-22B-02 and RB211-22B/MOD 72-8700. Effective Nov 28, 1983 - [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 78-19-01](https://openairdocs.org/ad/78-19-01): High Pressure Turbine Discs · Rolls-Royce RB211-22B-02 and RB211-22B/MOD 72-8700. Effective Sep 25, 1978 - [AD 76-26-01](https://openairdocs.org/ad/76-26-01): H.P. Turbine Disc · Rolls-Royce RB211-22B-02 and RB211-22B/MOD 72-8700. Effective Jan 3, 1977 - [AD 76-15-09](https://openairdocs.org/ad/76-15-09): Engine Shutdown · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700 and RB211-22C-02. Effective Jul 22, 1976 - [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 73-10-01](https://openairdocs.org/ad/73-10-01): VIGV Scheduling · Rolls-Royce RB211-22B-02, RB211-22B/MOD 72-8700 and RB211-22C-02. Effective May 8, 1973 All 71: https://openairdocs.org/tcds/E12EU/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Rolls-Royce RB211-535E4](https://openairdocs.org/engine/rolls-royce-rb211-535e4-series): 42 aircraft (registry code 54223) - [Rolls-Royce RB-211-22](https://openairdocs.org/engine/rolls-royce-rb-211-22-series): 8 aircraft (registry code 54554) - [Rolls-Royce RB211-535E437](https://openairdocs.org/engine/rolls-royce-rb211-535e437): 6 aircraft (registry code 54053) - [Rolls-Royce RB211535E4B37](https://openairdocs.org/engine/rolls-royce-rb211535e4b37): 4 aircraft (registry code 54054) - [Rolls-Royce RB211-22B-02](https://openairdocs.org/engine/rolls-royce-rb211-22b-02): 1 aircraft (registry code 54035) - [Rolls-Royce RB211-524B4](https://openairdocs.org/engine/rolls-royce-rb211-524b4-series): 1 aircraft (registry code 54591) - [Rolls-Royce RB211-22B](https://openairdocs.org/engine/rolls-royce-rb211-22b-series): 0 aircraft (registry code 54036) - [Rolls-Royce RB211-524B-02](https://openairdocs.org/engine/rolls-royce-rb211-524b-02): 0 aircraft (registry code 54037) - [Rolls-Royce RB211-524B219](https://openairdocs.org/engine/rolls-royce-rb211-524b219): 0 aircraft (registry code 54042) - [Rolls-Royce RB211-524B302](https://openairdocs.org/engine/rolls-royce-rb211-524b302): 0 aircraft (registry code 54039) - [Rolls-Royce RB211-524B402](https://openairdocs.org/engine/rolls-royce-rb211-524b402): 0 aircraft (registry code 54040) - [Rolls-Royce RB211-524BB02](https://openairdocs.org/engine/rolls-royce-rb211-524bb02): 0 aircraft (registry code 54038) - [Rolls-Royce RB211-524C219](https://openairdocs.org/engine/rolls-royce-rb211-524c219): 0 aircraft (registry code 54044) - [Rolls-Royce RB211-524D4](https://openairdocs.org/engine/rolls-royce-rb211-524d4-series): 0 aircraft (registry code 54047) - [Rolls-Royce RB211-524D419](https://openairdocs.org/engine/rolls-royce-rb211-524d419): 0 aircraft (registry code 54046) - [Rolls-Royce RB211-535C-37](https://openairdocs.org/engine/rolls-royce-rb211-535c-37): 0 aircraft (registry code 54052) - [Rolls-Royce RB211524B2B19](https://openairdocs.org/engine/rolls-royce-rb211524b2b19): 0 aircraft (registry code 54043) - [Rolls-Royce RB211524B4D02](https://openairdocs.org/engine/rolls-royce-rb211524b4d02): 0 aircraft (registry code 54041) - [Rolls-Royce RB211524C2B19](https://openairdocs.org/engine/rolls-royce-rb211524c2b19): 0 aircraft (registry code 54045) - [Rolls-Royce RB211524D4B19](https://openairdocs.org/engine/rolls-royce-rb211524d4b19): 0 aircraft (registry code 54048) - [Rolls-Royce RB211524D4B39](https://openairdocs.org/engine/rolls-royce-rb211524d4b39): 0 aircraft (registry code 54049) - [Rolls-Royce RB211524D4X19](https://openairdocs.org/engine/rolls-royce-rb211524d4x19): 0 aircraft (registry code 54050) - [Rolls-Royce RB211524D4XB1](https://openairdocs.org/engine/rolls-royce-rb211524d4xb1-series): 0 aircraft (registry code 54051) - [Rolls-Royce RB211535E4B75](https://openairdocs.org/engine/rolls-royce-rb211535e4b75): 0 aircraft (registry code 54055) - [Rolls-Royce RB211535E4C37](https://openairdocs.org/engine/rolls-royce-rb211535e4c37): 0 aircraft (registry code 54056) ## STCs approved under this data sheet (2) - [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc - [STC SE1516CE](https://openairdocs.org/stc/SE1516CE): Modification of lower fuel control box assembly to incorporate vibration isolators.. Trans World Airlines Inc --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.