TCDS E00066NE

______________________________________________________________________________________________________________ * Page 1 2 3 4 5 6 7 Revision 2 2 3 2 2 3 1 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "NOT APPLICABLE" NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00066NE TCDS NUMBER: E00066NE REVISION: 3 DATE: March 16, 2007 ROLLS-ROYCE plc MODELS: RB211 TRENT 553-61 RB211 TRENT 553A2-61 RB211 TRENT 556B-61 RB211 TRENT 556A2-61 RB211 TRENT 556-61 RB211 TRENT 556B2-61 RB211 TRENT 560-61 RB211 TRENT 560A2-61 Engines of models described herein conforming with this data sheet, (which is part of Type Certificate Number E00066NE), 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 plc Derby, England 1. MODELS RB211 Trent 553-61, 553A2-61 RB211 Trent 556-61, 556A2-61 RB211 Trent 556B-61, 556B2-61 RB211 Trent 560-61, 560A2-61 TYPE High by-pass turbofan (by-pass ratio of 8. 5), axial flow, three-shaft. Single stage low pressure fan driven by a five stage turbine. Eight stage intermediate pressure compressor driven by a single stage turbine. Six stage high pressure compressor driven by a single stage turbine. Annular combustion chamber. RATINGS (See NOTE 1) Maximum Continuous (1) Thrust pounds at sea level static Takeoff (5 minutes) (2) Thrust pounds at sea level static Equivalent bare engine thrust 44359 55780 56655 44359 58462 59350 44359 58462 (3) 59350 44359 61902 62740 (1) Flat rated to ISA +10 ºC for all altitudes. (2) Flat rated to ISA +15 ºC for all altitudes. (3) The Trent 556B-61 and 556B2-61 engines rated takeoff thrust is identical to the Trent 556-61 and 556A2-61engine at ISA sea level static conditions. The 556B-61 and 556B2-61 ratings provide increased thrust for takeoff at altitudes above sea level. The magnitude of this increased thrust varies with altitude, mach number and ambient temperatur e and provides the 560-61 and 560A2-61 ratings at 7341 feet and above. E00066NE Page 2 of 7 1. MODELS (continued) RB211 Trent 553-61, 553A2-61 RB211 Trent 556-61 556A2-61 RB211 Trent 556B-61 556B2-61 RB211 Trent 560-61 560A2-61 PRINCIPAL DIMENSIONS, inches Length From tip of spinner (minus rubber tip to tail bearing housing plug mount) Radius, maximum 184.6 66.5 - - - - - - - - - - - - CENTER OF GRAVITY- complete powerplant Aft from powerplant station 100 Below centerline Starboard from engine centerline CENTER OF GRAVITY- basic engine Aft from powerplant station 100 Below centerline Starboard from engine centerline 27.1 1.9 0.1 27.8 2.2 0.2 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - WEIGHT Dry powerplant Basic engine 13797 10930 - - - - - - - - - - - - Basic engine is the dry powerplant less n acelle, intake, cowl doors, CNA and thrust reverser. ENGINE PARTICULARS BUILD STANDARD RR Drawing Introduction Sheet (DIS) 553-61: 2207 Issue 4 553A2-61: 2230 Issue 1 556-61: 2208 Issue 4 556A2-61: 2231 Issue 1 556B-61: 2225 Issue 4 556B2-61: 2232 Issue 1 560-61: 2209 Issue 4 560A2-61: 2233 Issue 1 FUELS APPROVED FUELS See relevant Engine Operating Instructions for approved fuels. See relevant Engine Operating Instructions for approved oils. OILS APPROVED OILS OIL CONSUMPTION 1.32 U.S. pints/hour overall inflight maximum for unrestricted operation. OIL CAPACITY Nominal total system capacity Nominal oil tank capacity Minimum useable oil (including effect of attitude) 84.5 U.S. pints 49.0 U.S. pints 33.8 U.S. pints - - - - - - - - - - - - - - - - - - RB211 Trent 553-61, 556-61, 556B-61, 560-61, 553A2-61, 556A2-61, 556B2-61, and 560A2-61 COMPONENTS ELECTRONIC FULL AUTHORITY FUEL Fuel control Fuel pump Fuel metering unit IGNITION SYSTEM Ignition system plugs Ignition system units EQUIPMENT TRWEECS 500-04 TRWTPS 500MK2 TRWHMU 500MK2 Federal Mogul CH34761 Unison 430154 For identification of equipment approved for use on these engines, refer to Chapter 1 of appropriate Rolls-Royce Drawing Introduction Sheet (DIS) E00066NE Page 3 of 7 CERTIFICATION BASIS FAR 21.29 and FAR 33 effective Febr uary 1, 1965, as amended by FAR 33-1 through 33-19. Pursuant to FAR21.29(a)(1)(ii), the Type Certificate was issued in validation of the British Civil Aviation Authority Certification Standards JAR-E change 9 plus OP E/96/1 and E/97/1, which was found to provide a level of safety equivalent to that provided by FAR 33, Amendment 33-19. APPLICATION ISSUED/ MODEL DATE REVISED SURRENDERED RB211 TRENT 553-61 MAY 20, 1998 November 20, 2001 RB211 TRENT 556-61 MAY 20, 1998 November 20, 2001 RB211 TRENT 556B-61 JAN 25, 2000 November 20, 2001 RB211 TRENT 560-61 MAY 20, 1998 November 20, 2001 RB211 TRENT 553A2-61 January 3, 2003 September 16, 2003 RB211 TRENT 556A2-61 January 3, 2003 September 16, 2003 RB211 TRENT 556B2-61 January 3, 2003 September 16, 2003 RB211 TRENT 560A2-61 January 3, 2003 September 16, 2003 The aviation authority for the United Kingdom, the UK Civil Aviation Authority (CAA), originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E00066NE. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the 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 UK CAA or EASA airworthiness approval shall have a Joint Aviation Authorities (JAA) or EASA Form 1, Authorized Release Certificate. The JAA or EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E0066NE, is in a condition for safe operation and has undergone a final operational check. Additional guidance is contained in FAA Advisory Circular 21-23, "Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States." N O T E S NOTE 1. The engine ratings are based on static test stand operation under the following A & B conditions: A. (1) Compressor inlet air at 59 ºF and 29.92 Hg. (2) No aircraft accessory loads or optional air extraction. (3) 100% air intake recovery corrected from the datum air intake system defined by drawing ATF 16471 or approved alternatives. (4) Engine exhaust system defined by Common Nozzle Assembly RX95432-7 and Spacer Ring RX95425 (5) Turbine gas temperature and rotor speed limitations are not exceeded. B. Equivalent Bare Engine Thrust (LBF) The equivalent bare thrust (lbf) is rated th rust excluding the losses of propulsion fan duct And thrust reverser and jet pipe washed by the fan stream. NOTE 2. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS (%) 100% HP = 13,300 RPM 100% IP = 9,100 RPM 100% LP = 3,900 RPM Maximum takeoff (5 minutes) (See NOTE 18) HP 97.4 % IP 99.4 % LP 92.5 % E00066NE Page 4 of 7 NOTE 2. (continued) Maximum overspeed (20 seconds) HP (non-declared) IP (non-declared) LP (non-declared) Maximum reverse thrust (30 seconds) LP 69.0% NOTE 3. MAXIMUM PERMISSIBLE TEMPERATURES TURBINE GAS TEMPERATURE (TGT) ºC Starting Below 50% N3 (ground starting) 700 max. during start or relight Below 50% N3 (inflight starting) 850 Above 50% N3 850 Takeoff (5 minutes) 900 may be used up to 10 minutes in the event of engine failure Maximum continuous (unrestricted) 850 Overtemperature (20 seconds) 920 Oil Combined scavenge temperature (ºC) Minimum for starting for engines incorporating Modification Bulletin 79-E065 -40 for engines incorporating Modification Bulletin 79-D327 -20 Minimum for opening up 20 Maximum for unrestricted use 196 NOTE 4. FUEL AND OIL PRESSURE LIMITS Fuel MINIMUM FUEL PRESSURE Between sea-level and 41,000 feet, not less than 5 psig plus true fuel vapor pressure, measured at inlet to engine LP fuel pump. Oil Minimum oil pressure Ground idle to 70% HP rpm 25 psig Above 95% HP rpm 40 psig NOTE 5. MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS Air delivery for aircraft services, excluding powerplant anti-icing. The air is automatically scheduled from the engine HP stage 1 and HP stage 6 compressor bleed ports via two valves in the aircraft ducting, which select the appropriate supply in response to signals sensing HP compressor delivery pressure (P30) together with a synthesized HP compressor delivery temperature (T30Syn). With valve controller 6853A020000X5 the switchover from the HP6 to the HP1 compressor delivery port occurs at engine power settings where the following conditions are met: A. Out of icing conditions: When both the HP C delivery static pressure (P30S) is greater than (105 psi ± 5) gauge. B. In icing conditions: When both the HPC delivery pressure (P30S) reaches 130 psi ± 5) gauge and the HPC delivery temperature (T30syn) reaches 375ºC ± 5ºC. E00066NE Page 5 of 7 NOTE 5. (Cont’d) Maximum HP6 bleed (% of gas generator compressor flow); this bleed decreases linearly between the values listed below for the low idle and switchover points. A. Normal operation: (1) Low Idle and up to 1190 ºk TET 9.5 (2) At switchover point 4.0 B. Abnormal (one engine inoperative): (1) Low idle and up to 1210 ºk TET 16.25 (2) At 1400K TET 7.7 (3) At switchover point 4.6 Maximum HP1 bleed (4 of gas generator compressor flow); this bleed (HP1) decreases linearly between the values listed below for the switchover and 1700ºk TET. A. Normal operation: (1) At switchover point 4.0 (2) Up to1700 ºk TET 1.0 (3) At takeoff 1.0 B. Abnormal (one engine inoperative): (1) At switchover point 7.0 (2) Up to 1700 ºk TET 2.0 (3) At takeoff 2.0 Maximum LP bleed (% of fan flow) A. Normal and Abnormal (one engine inoperative): (1) From low idle and up to 1130 ºk TET .53 (2) Above 1650 ºk TET 0.25 Maximum HP3 bleed for powerplant anti-icing (% of HPC inlet flow); this bleed decreases linearly between the values listed below for the1000ºk TET and 1600ºk TET points. A. Normal and Abnormal (one engine inoperative): (1) From low idle to 1000 ºk TET 1.75% (2) At 1600 ºk TET and up to takeoff 1.5% NOTE 6. SHAFT POWER EXTRACTION LIMITATIONS Accessory drive provisions (continuous power as listed may be extracted under all engine operating conditions) TORQUE (lb. - in.) MODELS DRIVE ROTATION (AS VIEWED FROM GEARBOX) SPEED RATIO TO HP ROTOR SPEED CONTINUOUS MAXIMUM INSTANTANEOUS OVERHANG (in. - lb.) ALL MODELS STARTER IDG HYDRAULIC PUMP CW* CW CW .7967 .6807 .3744 2200 1500 6360 4505 2000 290 1300 183 * CW = CLOCKWISE CCW = COUNTERCLOCKWISE Max starter torque at 0ft varies with air temperature as follows: Air temperature Max torque (lb. - in,) -54 -40 ISA 6084 6077 5980 E00066NE Page 6 of 7 NOTE 7. The Full Authority Digital Engine Controller controls power settings. NOTE 8. Life limited parts are identified in the Engine manual. NOTE 9. This engine approval includes bare engine plus engine accessories, coolers, filters, harness, and instrumentation transmitters as defined in the appropriate RR DIS. Hydraulic pumps and IDG are aircraft supply. NOTE 10. RB211 series manuals under CAA requirements accepted as equivalent to FAR 33.4 and FAR 33.5 requirements are: MODEL RB211- OPERATING INSTRUCTIONS MAINTENANCE MANUAL INSTALLATION MANUAL ENGINE MANUAL TRENT 553-61 TRENT 556-61 TRENT 556B-61 TRENT 560-61 TRENT 553A2-61 TRENT 556A2-61 TRENT 556B2-61 TRENT 560A2-61 OI - TRENT - A340 OI - TRENT - A340 OI - TRENT - A340 OI - TRENT - A340 OI - TRENT - A340 OI - TRENT - A340 OI - TRENT - A340 OI - TRENT - A340 M - TRENT - A340 M - TRENT - A340 M - TRENT - A340 M - TRENT - A340 M - TRENT - A340 M - TRENT - A340 M - TRENT - A340 M - TRENT - A340 DNS 62612 DNS 62612 DNS 62612 DNS 62612 DNS 62612 DNS 62612 DNS 62612 DNS 62612 E - TRENT - A340 E - TRENT - A340 E - TRENT - A340 E - TRENT - A340 E - TRENT - A340 E - TRENT - A340 E - TRENT - A340 E - TRENT - A340 Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or, for approvals made before September 28, 2003 by the United Kingdom Civil Aviation Authority. Any such documents including those approved under a delegated authority, are accepted by the FAA and are considered FAA approved. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. • Technical Variances These approvals pertain to the type design only. NOTE 11. These engines meet the smoke and gaseous emission requirements of Part 34. NOTE 12. The engine is fitted with a Digital Electronic Engine Fuel Control system in which the software meets the "critical" standard of RTCA DO-178B. NOTE 13. In icing conditions, the engine may be operated satisfactorily at LP rotor speeds (N1) down to low idle. Minimum corresponding N1 at low idle for these engines is 17.6 percent in flight and 15.4 percent for ground running. NOTE 14. These engines are fitted with an independent IP and LP spool overspeed governor. Dispatch with this item unserviceable is not permitted. NOTE 15. These engines satisfy the certification base as defined in this Data Sheet when operating with the FADEC in reversionary control mode. E00066NE Page 7 of 7 NOTE 16. VARIANTS RB211 TRENT 553-61 Basic model. RB211 TRENT 556-61 and 560-61 Same as basic model except for increased takeoff thrust r a t i n g . RB211 TRENT 556B-61 Same as 556-61 model except for increased takeoff thrust ratings at altitude. RB211 TRENT 553A2-61 A derivative of the RB211 TRENT 553-61 with improved fuel consumption. RB211 TRENT 556A2-61 A derivative of the RB211 TRENT 556-61 with improved fuel consumption. RB211 TRENT 556B2-61 A derivative of the RB211 TRENT 556B-61 with improved fuel consumption. RB211 TRENT 560A2-61 A derivatiave of the RB211 TRENT 560-61 with improved fuel consumption. NOTE 17. The RB211 TRENT 500 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 dispatch and maintenance requirements for the engine control system. Fault Class 1 Level A: No dispatch allowed Fault Class 1 Level B: Dispatchable; maximum operating interval for Fault Class 1 Level B fault(s) is 300 operating hours Fault Class 2: Dispatchable; ma ximum operating interval for Fault Class 2 fault(s) is 500 operating hours Fault levels Class 1 and 2 constitute Rolls-Royce nomenclature. The airframe manufacturers may use different nomenclature in adapting these fault categories to the aircraft maintenance and display systems; however, the maximum operating intervals are restricted as shown above. NOTE 18. The takeoff rating and its associated operating limitations may be used for up to 10 minutes in the event of engine out contingency, but their use is otherwise limited to no more than 5 minutes. ---END---