# TCDS E5EU: Rolls-Royce Deutschland Ltd & Co KG - Type: Type certificate data sheet - Status: Current - Holder: Rolls-Royce Deutschland Ltd & Co KG - Revision: 9 - Revised: March 23, 2007 - Product: Engine - Certification basis: Part 13, Part 33, CAR 10 - Registered aircraft: 1, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/83/aa/83aa87a6ffa12f33fd16572a405f4068d173df69049b13cd42abdfac9a6f9cb6 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4D410BD77437E108862572A500732FE3.0001 - Page: https://openairdocs.org/tcds/E5EU ## Models (5) As the data sheet lists them. - Dart 542-4 - Dart 542-10 - Dart 542-4K - Dart 542-10K - Dart 542-10J ## 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 No. 1 2 3 4 Rev. No. 9 9 7 9 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "NOT APPLICABLE" NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E5EU TCDS E5EU Revision: 9 DATE: March 23, 2007 Rolls-Royce Deutschland Ltd & Co KG MODELS: Dart 542-10, 542-10J, 542-10K 542-4, 542-4K Engines of models described herein conforming with this data sheet (which is a part of type certificate No. E5EU) 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 Civil Air Regulations provided they are installed, operated and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Manufacturer Rolls-Royce Deutschland Ltd & Co KG Postfach 1536 D-15827 Dahlewitz Germany (formerley Rolls-Royce Limited, Derby, England) Model: Dart 542-10, 542-10J 542-10K 542-4 542-4K Type: Turboprop 2-stage centrifugal compressor 3-stage turbine 7 combustion chambers .0775 to 1 reduction gearing - - - - - - - - - - - - - - - - - - - - - - - - Rating Max. continuous at sea level, equivalent shaft hp., shaft hp., jet thrust, (lb.), r.p.m. 2559-2305-637-15000 - - - - - - Takeoff (5 min.) at sea level, equivalent shaft hp., shaft hp., jet thrust, (lb.) r.p.m. 2559-2305-637-15000 - - - - - - With water/methanol injection 2966-2680-715-15000 - - - - - - Propeller shaft type SBAC No. 4½ - - - - - - Fuel control Lucas CCU 73/58 BU - - - - - - Water/methanol control unit Rolls-Royce RK 38599 - - RK 38599, RK 40898 - - Fuel See NOTE 6 - - - - - - Oil capacity (4.5 U.S. gal. integral oil tank) - - - - - - Oil types See relevant RR Operating Instruction Manual - - - - Principal dimensions: Length, overall, in. 99.5 100.24 99.5 100.24 Diameter, in. 37.4 - - - - - - C.G. location: Aft of mounting feet, (in.) 2.0 1.5 2.0 1.5 TCDS E5EU 2 Rating (Continued) 542-10, 542-10J 542-10K 542-4 542-4K Weight (dry), lb. (includes all controls, exhaust unit, ignition system, thermocouples, oil tank and fuel pump) 1385 1405 1385 1405 Ignition system Igniter Box: Rotax NB 38 or AEI Type C34TS - - - - - - Igniters: Champion FHE-19-6H (RR Type CR-104), Smith Type LR 104, AC YA-20 - - - - - - NOTES 1 through 12 Certification Basis: CAR 10 and British Civil Airworthiness Requirement s Section C, Issue 5 dated July 1, 1962, (BCAR Section C, Issue 5, is equivalent to the applicable parts of CAR Part 13, effective June 15, 1955, and amendments 13-1 through 13-5). Type Certificate No. 297 amended July 16, 1962 for basic Dart 542. Approval of this engine subsequently rescinded as all basic Dart 542 engines converted to Dart 542-10 standard. Dart 542-10J & 10K-4K comply with BCAR Section C, Issue 6 dated June 15, 1966, which is equivalent to Part 33-L. Type Certificate (Import) No. E5EU issued for Dart 542-10, 542-4, October 15, 1965, amended to include 542-10J & 10K on July 15, 1968, and 542-4K on January 7, 1970. Date of Application for Type Certificate July 16, 1962. The aviation authority for Germany, Luftfahrt-Bundesa mt, type certificated this engine certificate. The FAA validated this product under U.S. Type Certificate Number E5EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. Import Requirements: To be considered eligible for installation on U.S. re gistered aircraft, each new engine to be exported to the United States with Luftfahrt-Bundesamt (Germany) 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 E5EU, is in a condition for safe operation and has undergone a final operational check. Additional guidance is contained in FAA Advisory Ci rcular 21.23, Airworthiness Certification of Civil Aircraft, Engines, Propellers and Related Products, Imported into the United States. NOTES NOTE 1. Maximum permissible temperatures: Turbine gas temperatures: 542-10 542-10J, -10K 542-4, -4K Takeoff (wet) (5 minutes) (890°C) 940°C (940°C) Takeoff (dry) (865°C) - - - - Maximum continuous (905°C) 915°C (915°C) Maximum transient (starts) (930°C) - - - - Maximum overtemperature (5 second limit) (1000°C) (1000°C) (1000°C) Oil inlet temperature range (-15° to 120°C) - - - - NOTE 2. Fuel and oil pressure limits: Fuel supply pressure at engine fuel inlet, varying with flow per RR curve HK 30017, Issue 3. Oil pressure varies with oil inlet temperature; normal 14 to 35 p.s.i.g. in flight; with 9 p.s.i.g. minimum in flight. NOTE 3. Engine ratings are based on standard conditions with no air bleed or aircraft accessory power extraction, 60°F, 29.92 in. Hg., and Pw/Po = .01 at sea level within limiting gas temperatures. With dry air, T.O. power is increased less than .5% and M.C. power by 1.3%. Jet thrust is converted to equivalent shaft hp by dividing the thrust value by a factor of 2.5. The output values are the minimum acceptable and are based on the use of Rolls-Royce exhaust cone RK 25226 or RK 21556 and with 12 thermocouples located in the intermediate turbine guide vanes. NOTE 4. Water/methanol injection is optional and is utilized through auto matically varied flow to provide a constant level of power output for take-offs. The w/m fluid should be a 63/37 mixture of water and methyl alcohol for all models. (Rolls-Royce TCDS E5EU 3 AEP-1W/M Issue 5 or equivalent.) The water used is distilled or contains a maximum of 10. ppm solids, and the methyl alcohol is British D Eng RD 2481 or equivalent. The w/m flow varies up to a maximum of 805 gph (U.S.) for 542-10 series and up to 859 U.S. gph for 542-4. W/m injection should not be used at ambient temperatures lower than -22°F (- 30°C). The takeoff power reduces automatically with altitude since the w/m control does not compensate power output for the effects of altitude. NOTE 5. Accessory provisions on engine: (Oil c ooler and air inlet are engine mounted) Drive Rotation (facing drive) (C-clockwise) (CC-counter clockwise) Speed Ratio to Turbine Continuous Torque* (in. - lb.) Static Torque** (in. - lb.) Maximum Overhang (in. - lb.) Power takeoff (175 hp max.) CC 0.345 2100 6350 to 6890 128 Propeller governor: CU 97 CC 0.188 138 1380 190 Starter: Rotax 14203 CC 2.0 272 1000 84 Fuel pump: Lucas GB242/9/BV CC 0.188 110 780 34 * Continuous torque values are based on takeoff power at sea level **Maximum torque of weak link without permanent set, or the clutch setting for the starter. NOTE 6. Fuels to the following specifications, or others shown in the approved Operating Instructions F-Da10YS and F- Da10C are eligible for these engines: British D.Eng. R.D. - 2494, 2486, 2498, 2453, 2454. Canadian - 3-GP-23 g, 3-GP-24f, 3-GP-22g. American - ASTM D1655-72 JET A or A-1 or JET B. MIL-T-5624H Grade JP5, MIL-T-5624H Grade JP4. IATA - Kerosene Type Fuel (1969) and JP4 Type (1969). French - AIR 3405/C, AIR 3404/B, AIR 3407/B. The following departures from Specification D.Eng.RD 2494 are acceptable:- Flash point, maximum 70°F, Mercapton Sulphur maximum 0.016 percent by weight. The mixing of approved fuels is permitted without restriction. No adjustment of the engine controls is necessary and no loss of performance occurs. The only optional additives which may be used in approved fuels are as follows:- 1. Anti-static additive Shell ASA 3 in concentrations not exceeding 1.0 p.p.m. 2. Anti-icing additive to specification D.Eng.R.D. 2451 or MIL-I-27686E in concentrations not exceeding 0.15% volume. 3. HITEC E515 (formerly Santolene C) anti-corrosion/lubric ity additive up to a concentration of 5 lbs per 42000 U.S. gallons. 4. TOLAD 245 anti-corrosion additive up to a concentration of 12 lbs per 42000 U.S. gallons. 5. Biobor J.F. biocide on an intermittent or non-continuous basis at a concentration not exceeding 270 p.p.m. (total Boron content not to exceed 20 p.p.m.). The treated fuel may be burnt off in the engine provided it is not contaminated by microbiological debris. For continuous treatment Biobar J.F. biocide additive ma y be used in accordance with the appropriate Rolls-Royce instructions in concentrations not exceeding 135 p.p.m. NOTE 7. These engines meet FAA requirements for ic ing protection, for adequate turbine disc integrity, for rotor blade containment, and do not require external armoring. NOTE 8. Propellers used with this engine must have functioning characteristics which are compatible with the engine and its control system. NOTE 9. Maximum air bleed for aircraft services is 1.5% of no-bleed mass flow. NOTE 10. Maximum overspeed limit is 16500 r.p.m. for 20 seconds. When this limit is exceeded the engine requires inspection as detailed in the Rolls-Royce Maintenance Manual. NOTE 11. The maximum allowable horsepower cleared for the engine to cover operation at low ambient air temperature and/or ram conditions is 3000 shp. TCDS E5EU 4 NOTE 12. The above models incorporate the following general characteristics: Model Characteristics Dart 542 Original basic model for use in Prototype Japanese YS-11 aircraft - superseded by 542-10. Dart 542-10 Production standard for YS-11 aircraft (Japan ) used with 14' -6" Dowty Rotol propeller. Approved October 15, 1965. Dart 542-10J Variant for YS-11 aircraft with improved turbine blading and higher TGT limits. Dart 542-10K Variant for YS-11 aircraft. As 542-10J but with strengthened reduction gear. Dart 542-4 Model for installation in CONVAIR 240D, 340D and 440D aircraft. Minor installation changes from 542- 10 model and with an increased max. continuous TGT limitation. Approved October 15, 1965. Dart 542-4K Variant CONVAIR 600 and 640 aircraft. As 542-4 but with strengthened reduction gear. NOTE 13. 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 Luftfahrt-Bundesamt (Germany) or 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 (22, in force first) - [AD 2008-16-05](https://openairdocs.org/ad/2008-16-05): Intermediate pressure turbine (IPT) disk · Rolls-Royce Deutschland Dart 528-7E, Dart 528D-7E, Dart 529-7E and 29 more. Effective Sep 4, 2008 - [AD 2007-03-13](https://openairdocs.org/ad/2007-03-13): High pressure turbine (HPT) blade platforms and shrouds · Rolls-Royce Deutschland Dart 528-7E, Dart 528D-7E, Dart 529-7E and 27 more. Effective Mar 19, 2007 - [AD 2003-17-11](https://openairdocs.org/ad/2003-17-11): Sermetel coating (Omat 7/46) · Rolls-Royce Deutschland Dart 528-7E, Dart 529-7E, Dart 529-7H and 29 more. Effective Sep 30, 2003 - [AD 2001-19-06](https://openairdocs.org/ad/2001-19-06): High Pressure Turbine Discs · Rolls-Royce Deutschland Dart 525, Dart 525F, Dart 528-7E and 31 more. Effective Oct 15, 2001 - [AD 99-27-04](https://openairdocs.org/ad/99-27-04): Low Torque Switches · Rolls-Royce Deutschland Dart 506, Dart 510, Dart 511 and 38 more. Effective Feb 28, 2000 - [AD 99-04-09](https://openairdocs.org/ad/99-04-09): High Pressure Turbine Disk · Rolls-Royce Deutschland Dart 525, Dart 525F, Dart 526 and 35 more. Effective Feb 25, 1999 - [AD 98-04-13](https://openairdocs.org/ad/98-04-13): Propeller Low Torque Switch · Rolls-Royce Deutschland Dart 506, Dart 510, Dart 511 and 43 more. Effective Mar 24, 1998 - [AD 93-15-09](https://openairdocs.org/ad/93-15-09): Servo Fuel Pipe · Rolls-Royce Deutschland Dart 506, Dart 510, Dart 511 and 40 more. Effective Sep 7, 1993 - [AD 88-21-06](https://openairdocs.org/ad/88-21-06): High Pressure Impellers · Rolls-Royce Deutschland Dart 506, Dart 510, Dart 511 and 35 more. Effective Nov 6, 1988 - [AD 85-03-03 R1](https://openairdocs.org/ad/85-03-03-R1): Low Pressure Impeller · Rolls-Royce Deutschland Dart 506, Dart 510, Dart 511 and 38 more. Effective Jan 6, 1986 - [AD 78-24-01 R1](https://openairdocs.org/ad/78-24-01-R1): Control Box Mounting Bolt Failure · Rolls-Royce Deutschland Dart 506, Dart 510, Dart 511 and 34 more. Effective May 12, 1983 - [AD 73-12-03 R1](https://openairdocs.org/ad/73-12-03-R1): Engine Mounting Foot Stud · Rolls-Royce Deutschland Dart 542-10, Dart 542-10J and Dart 542-10K. Effective Dec 10, 1981 - [AD 80-23-01](https://openairdocs.org/ad/80-23-01): Low Pressure Impellers · Rolls-Royce Deutschland Dart 506, Dart 510, Dart 511 and 38 more. Effective Oct 30, 1980 - [AD 78-07-08](https://openairdocs.org/ad/78-07-08): Flame Tube Liners And Suspension Pins · Rolls-Royce Deutschland Dart 542-10 and Dart 542-4. Effective May 3, 1978 - [AD 77-21-05](https://openairdocs.org/ad/77-21-05): High Pressure Turbine Discs · Rolls-Royce Deutschland Dart 527, Dart 528-7E, Dart 528D-7E and 28 more. Effective Nov 11, 1977 - [AD 72-16-05](https://openairdocs.org/ad/72-16-05): Impellers · Rolls-Royce Deutschland Dart 506, Dart 510, Dart 511 and 35 more. Effective Dec 4, 1972 - [AD 72-23-02](https://openairdocs.org/ad/72-23-02): Impeller · Rolls-Royce Deutschland Dart 542-10, Dart 542-10J, Dart 542-10K and 2 more. Effective Oct 26, 1972 - [AD 70-25-06](https://openairdocs.org/ad/70-25-06): Engine Propeller Shaft · Rolls-Royce Deutschland Dart 542-10, Dart 542-10J, Dart 542-10K and 2 more. Effective Dec 7, 1970 - [AD 67-27-06](https://openairdocs.org/ad/67-27-06): Fuel and Oil Hoses · Rolls-Royce Deutschland Dart 542-10 and Dart 542-4. Effective Oct 3, 1967 - [AD 63-07-04](https://openairdocs.org/ad/63-07-04): Air Casing · Rolls-Royce Deutschland Dart 506, Dart 510, Dart 511 and 43 more. Effective May 2, 1963 - [AD 72-14-06](https://openairdocs.org/ad/72-14-06): Impellers, · Rolls-Royce Deutschland Dart 542-10, Dart 542-10J, Dart 542-10K and 2 more - [AD 2007-02-07](https://openairdocs.org/ad/2007-02-07) (historical): Intermediate pressure turbine (IPT) disk · Rolls-Royce Deutschland Dart 528-7E, Dart 528D-7E, Dart 529-7E and 29 more. Effective Feb 26, 2007 ## Registered aircraft by registry model (OpenAirDocs) - [Rolls-Royce DART-542](https://openairdocs.org/engine/rolls-royce-dart-542-series): 1 aircraft (registry code 54522) - [Rolls-Royce DART-542-10](https://openairdocs.org/engine/rolls-royce-dart-542-10): 0 aircraft (registry code 54134) - [Rolls-Royce DART-542-10J](https://openairdocs.org/engine/rolls-royce-dart-542-10j): 0 aircraft (registry code 54135) - [Rolls-Royce DART-542-10K](https://openairdocs.org/engine/rolls-royce-dart-542-10k): 0 aircraft (registry code 54136) - [Rolls-Royce DART-542-4](https://openairdocs.org/engine/rolls-royce-dart-542-4): 0 aircraft (registry code 54137) - [Rolls-Royce DART-542-4K](https://openairdocs.org/engine/rolls-royce-dart-542-4k): 0 aircraft (registry code 54138) ## STCs approved under this data sheet (2) - [STC SE905EA](https://openairdocs.org/stc/SE905EA): Repair and modification of compresor outlet and interstage cases.. Airwork Corporation - [STC SE748EA](https://openairdocs.org/stc/SE748EA): Installation of GLA ignition exciter.. General Laboratory Association 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.