TCDS E12EU

* 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.