# TCDS E14NE: Rolls-Royce Limited - Type: Type certificate data sheet - Status: Current - Holder: Rolls-Royce Limited - Revision: 3 - Revised: June 6, 2011 - Product: Engine - Certification basis: Part 21, Part 33 - Data sheet PDF: https://openairdocs.org/files/sha256/e2/b1/e2b142d949a69013744926e0a47e842508e65bdaa8407641b99ab1728f7ea7e6 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/A225608105900CFD862578B5004A9FE5.0001 - Page: https://openairdocs.org/tcds/E14NE ## Models (1) As the data sheet lists them. - GEM Mk. 510 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E14NE Revision 3 Rolls-Royce, Ltd. GEM Mk. 510 June 6, 2011 NOTE 15 This type certificate is cancelled effective June 6, 2011 and is not valid for aircraft manufactured after this date. This cancellation also invalidates, and precludes issuance of, any U.S. Certificates of Airworthiness. TYPE CERTIFICATE DATA SHEET NO. E14NE Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E14NE) and other approved data on file with the Federal Aviation Administration (FAA) meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations (FARs), provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Type Certificate Holder Rolls-Royce Limited Leavesden, England Model Mk. 510 Type Turboshaft with free power turbine. 4 stage axial flow LP compressor driven by single stage turbine. Single stage centrifugal HP compressor driven by single stage turbine. Two stage power turbine driving double helical epicyclic main reduction gearbox, ratio 4.5 to 1. Annular reverse flow combustion chamber. Ratings (see Note 7) Maximum continuous at sea level static, output SHP 890 Takeoff (5 mins. at sea level static, output SHP 1000 30 minute Helicopter rating at sea level static, output SHP 1075 2-1/2 minute helicopter rating at sea level static, output SHP 1135 Fuel (see Note 8) Fuel control - Plessey fuel control unit incorporating protective control unit GFS 204 Mk.1 Fuel control - Plessey free turbine governor FTG 202 Mk. 1 Oil Tank capacity - US pints 9.6 Usable oil - US pints 6.6 Type (see Note 9) Aeroshell turbine oil 555 Castrol 580 gas turbine oil Turbonycoil 150 NA Ignition System Igniter Unit, Smiths type 0802 KIU/1 Two igniter plugs, AC Delco type YB 63-1 Page No. 1 2 3 4 Rev. No. 3 2 2 2 E14NE 2 Principal Dimensions (inches) Length 43.4 Height 23.5 Width 22.6 Weight (lbs.) 407 (dry, includes essential engine-mounted accessories but excludes aircraft mounted torque indication units - see Note 10) Center of gravity location - (inches) (aft of engine gearbox/front mounting face) 20.5 Certification basis FAR 21.29 and FAR 33 effective Fe bruary 1, 1965, as amended by Amendments 33-1 through 33-6, inclusive. Pursuant to FAR 21.29(a)(i)(ii) the type certificate was issued in validation of the British Civil Aviation Authority (CAA) certification to British Civil Airworthiness Requirements, BCAR Section 5 Issue 10, dated March 22, 1977, which were found to provide a level of safety equivalent to the above FAR 33 regulations. Import requirements Each individually imported engine must be accompanied by a Rolls-Royce Limited/CAA approved "Inspection and Test Certificate" signed by a person authorized by the CAA and containing the following statement: "The engine covered by this certificate conforms to Type Certificate E14NE and is in condition for safe operation and has been subjected by the manufacturer to a final operational check." Note 1. Gas Generator Speed Limitations - (rpm) 2-1/2 minute rating 44,600 30-minute rating 44,300 Takeoff (5 mins. rating) 44,000 Maximum continuous rating 43,400 Transient (20 sec.) 46,000 Ground idle 20690/28015 Note 2. Output Shaft Speed Limitations (rpm) Minimum Maximum 2-1/2 minute rating 5210 6260 30-minute rating 5230 6280 Takeoff (5 mins.) rating 5240 6300 Maximum continuous rating 5260 6420 Transient (20 seconds) — 6800 Maximum for autorotation (no load) — 6680 Note 3. Output Shaft Torque Limitations - (lb.-ft.) 2-1/2 minute rating 1000 30-minute rating 950 Takeoff (5 min.) rating 900 Maximum continuous rating 850 Transient (20 secs.) 1200 Note 4. Temperature Limitations (°C) Power Turbine Inlet Temperature (measured at stage 1 power turbine nozzle) 2-1/2 minute rating 690 30-minute rating 675 Takeoff (5 mins.) rating 660 Maximum continuous rating 635 Maximum idling 550 Momentary maximum during starts 720 3 E14NE Fuel Temperature (measured at engine inlet) - maximum 50 Oil Temperature (measured at oil cooler outlet) - maximum 140 Note 5. Fuel and Oil Pressure Limitations Fuel - Minimum, measured at engine inlet: - Boost pump operative: 9 psia above fuel true vapor pressure. - Boost pump inoperative: with AVTUR fuel, 6.3 psia at vapor to liquid (V/L) ratio less than 0.19. with AVTAG fuel. 8.2 psia at V/L ratio less than 0.19. Oil - (psid) (measured at oil filter outlet)* Normal (P 2 + 10) Minimum to complete flight (P 2 + 5) Minimum at ground idle (P 2 + 5) *differential oil pressure related to P2 engine air pressure Note 6. Bleed Air and Accessory Drive Limitations Maximum air bleed for aircraft services is 3% of no-bleed mass flow over whole range of HP system RPM subject to limiting power turbine inlet temperature not being exceeded. A separate air bleed is provided via an engine mounted valve for aircraft intake anti-icing use. This supplies approximately 1.1% of no-bleed flow subject to usage limitations as detailed in Operating Instructions Manual. Accessory Drive Provisions Torque (lb.-in.) Drive Type Rotation* Speed** Cont Overload Overhang (In.-Lb.) Starter - as starter pad RS 623 C 0.247 243 729 1301 Starter - as generator pad RS 623 C 0.247 168 336 1301 Spare drive RS 623 CC 0.141 84 432 119 *C - Clockwise, and CC - Counter Clockwise; facing pad. **Speed is related to HP compressor system. NOTE 7. Engine ratings are based on calibrated test stand performance under the following conditions: Nominal output shaft speed of 6164 rpm. Static sea level standard conditions of 59°F and 29.92 in. Hg. Air Intake - front mounting shroud WD 793-106/107, intake flare WD 793-67 debris guard WD 793-78 or approved alternative Exhaust Unit - WD 532-112 or approved alternative All optional air bleeds closed. Aircraft service accessory drives unloaded. Additional performance parameters are contained in technical specification TSC 223 (Mk. 510). NOTE 8. Approved fuels and fuel additives are listed in RR Operating Instructions Manual - see Note 13. NOTE 9. Alternate brand oils to those listed are permitted when authorized by CAA approved RR Service Bulletin. Oils reclaimed from the above approved brands to RR endorsed procedures may also be used. NOTE 10. The engine approval includes the following airframe-mounted items of the torque indicating system which are listed in the RR engine Drawing Introduction Sheet (DIS) No. 12: torque electronic unit and torque indicator, which weigh 2.2 lbs. and 2.1 lbs. respectively. E14NE 4 NOTE 11. The installation must be such that: Ingestion of birds is prevented. Ingestion of hail greater than 1 inch diameter is prevented. Windmilling does not cause the HP rotor system to rotate. NOTE 12. Life limited parts and accountability methods are identified in Rolls-Royce GEM Engine Service Bulletin No. 6000. NOTE 13. Gem series manuals approved under BCAR requirements accepted as equivalent to FAR 33.5 requirements are as follows: Installation Instructions Gem Mk. 510 Installation Manual No. IM10. Operating Instructions Gem Mk. 510 Operat ing Instructions, Publication ref. 1915. Maintenance Gem Mk. 510 E ngine Maintenance Manual Overhaul Gem Mk. 510 Overhaul Manual Performance Gem Mk. 510 Technical Sp ecification No. TSC 229 and TP 83. Parts Catalogue Gem Mk. 510 Illustrated Parts Catalogue NOTE 14. Overhaul of engine is not authorized unless the Overhaul Manual is available; otherwise, rebuilt engines utilizing new engine tolerances may be provided by the manufacturer. .....END..... ``` ## ADs None name its models. --- 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.