# TCDS E1EU: Bristol Siddeley Engines Ltd. - Type: Type certificate data sheet - Status: Current - Holder: Bristol Siddeley Engines Ltd. - Revision: 2 - Revised: March 28, 2007 - Product: Engine - Certification basis: Part 13 - Data sheet PDF: https://openairdocs.org/files/sha256/a1/9b/a19bf0a70be544dd4fb754a0338f6141cc61df220d0b29d3c6de6ca3aed6d5bd - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/BB9655E9D3003DCE862572B30053511E.0001 - Page: https://openairdocs.org/tcds/E1EU ## Models (7) As the data sheet lists them. - Gnome H.1200 Mk. 640A - Gnome H.1200 Mk. 610 - Gnome H.1000 Mk. 510 - Gnome H.1200 Mk. 640 - Gnome H.1000 Mk. 511 - Gnome H.1200 Mk. 641A - Gnome H.1200 Mk. 641 ## 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 E1EU Revision 2 Gnome H.1000 Mks 510, 511 Gnome H.1200 Mk. 610 Mks. 640, 641 Mks. 640A, 641A March 28, 2007 TYPE CERTIFICATE DATA SHEET NO. E1EU Engines of models described herein conforming with this data sheet (which is part of type certificate no E1EU) and other approved data on file with the Federal Aviation Agency, 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. Type Certificate holder: Bristol Siddeley Engines Limited Leaves den Hertfordshire, England Model H.1000 Mk.510 H.1000 Mk.511 H.1200 Mk.610 H.1200 Mks.640, 641,640A,641A Type Axial flow, free turbine turboshaft Ten stage compressor. Annular combustion chamber. Two stage gas generator turbine. Single stage power turbine. 2.926:1 main reduction gearbox and forward drive shaft. - - - - - - - - —— Ratings (see Notes 4 and 11) at nominal power speed, r.p.m. 19300 19300 19500 19500 Max. continuous at sea level; output s.h.p. 875 895 1020 1050 Takeoff (5 mins) at sea level; output s.h.p. 972 1020 1215 1250 30-min. Helicopter rating at sea level; output s.h.p. —— —— —— 1250 Fuel control Hawker Siddeley Dynamics electrical Computer and Throttle Actuator with Lucas hydraulic Integrated Fuel system. Computer PQ.2154/2 - - - - PQ.2163 PQ.2158 Throttle Actuator PQ.2142/2 - - - - - - - - - - - - Integrated Fuel System IFS.100 - - - - IFS.102 - - - - Fuel 1. Aviation Kerosene Specs British: D.Eng.R.D.2482,2494 American: ASTM.D1655-61T Type A, or A-1 Canadian: 3-GP-23e type 1 - - - - - - - - - - - - Page No. 1 2 3 4 Rev No. 2 2 2 2 Reformatted 2/94. E1EU Page 2 Model (cont.) H.1000 Mk.510 H.1000 Mk.511 H.1200 Mk.610 H.1200 Mks.640 641,640A,641A Fuel (cont.) 2. Aviation Wide Cut Spec. British: D.Eng.R.D.2486 American: ASTM.D.1655-61T Type B Canadian: 3-GP-22e type 2 - - - - - - - - - - - - 3. High Flash Aviation Kerosene Specs. British: D.Eng.R.D.2488,2498 Canadian: 3-GP-24d - - - - - - - - —— No fuel control adjustment is required when changing from one type of fuel to another or when using a mixture of fuels. - - - - - - - - - - - - Oil Esso Aviation Turbo Oil 35 Esso Turbo Oil 35 Esso Turbo Oil TJ-15 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Principal dimensions Length, ins. 66 - - - - - - - - 59 Max. diameter, ins. 16 - - - - - - - - - - - - Weight (dry), lb. (includes essential engine-mounted, engine accessories, starter and bullet, turbine bucket guard; also main reduction gearbox, forward drive shaft and pedestal bearing for Mks.510, 511 and 610 models) 463 - - - - 484 345 a) Computer (a/c mounted), lb. 18 - - - - - - - - - - - - b) H.E. Ignition Unit (a/c mounted), each, lb. 4 - - - - - - - - - - - - C.G. location, excluding items (a) and (b) with starboard exhaust - - - - - - - - with down exhaust Aft of front mount centerline, ins. 25.0 - - - - - - - - 17.8 Below engine centerline, ins. 1.0 - - - - - - - - 0.7 Offset to Port, ins. 2.3 - - - - - - - - 0.4 Ignition Systems (24 volts D.C., 150 watts max.) Two A.E.I. High Energy Ignition Units type C44TS/1 - - - - - - - - - - - - Igniter plugs Smith type 901-1 - - - - - - - - - - - - "- - - -" indicates same as preceding model "——" indicates does not apply CERTIFICATION BASIS CAR 10 and British Civil Airworthiness Requirements, Section C. (The BCAR Section C is equivalent to U.S. CAR Part 13 effective June 15, 1956 as amended by 13-1 through 13-5). Type Certificate No. E1EU issued April 28, 1964. Date of application for Type Certificate October 10, 1961. The aviation authority for the United Kingdom (UK), the UK Civil Aviation Authority (CAA), originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E1EU. 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 E1EU, is in a condition for safe operation and has undergone a final operational check. NOTE 1. Maximum permissible gas generator operating speeds (r.p.m.) are as follows: Maximum continuous 25750 - - - - 25300 - - - - Takeoff 26300 - - - - - - - - - - - - 30 minute helicopter rating —— —— —— 26300 NOTE 2. Maximum permissible temperatures: Power Turbine Inlet* Takeoff 1103ºF (595ºC) 1157ºF (625ºC) 1265ºF (685ºC) 1265ºF (685ºC) 30-mins. power —— —— —— 1265ºF (685ºC) Maximum continuous 1049ºF (565ºC) 1103ºF (595ºC) 1175ºF (635ºC) 1175ºF (635ºC) Starting 1238°F (670°C) 1238°F (670°C) 1238°F (670°C) 1238°F (670°C) Oil Inlet 212ºF (100ºC) 212ºF (100ºC) 212ºF (100ºC) 230ºF (110ºC) * The power turbine inlet gas temperatur e is measured by (8) thermocouples mounted in a radial plan e in the second stage turbine casing. NOTE 3. Fuel and oil pressure limits Fuel, minimum at engine inlet: See Bristol Siddeley Report DDR No. 88 - - - - See Bristol Siddeley Report DDR No. 100 - - - - Oil: Engine, at ground idling and in autorotation 15 p.s.i.g. minimum Normal operating range 35-45 p.s.i.g. Minimum to complete flight 30 p.s.i.g. Main Reduction Gearbox Normal operating range 80-90 p.s.i.g. Minimum to complete flight 60 p.s.i.g. NOTE 4. Accessories Drive provisions Direction of Maximum Torque (in-lb) Drive Type Rotation * Speed ** Continuous Static Starter Special cc 1.0 180 336 Centrifugal Fuel Filter Special cc 0.1602 5 50 Gas Gen. Tachometer SBAC RS.307 c 0.1602 7 50 Power Turbine (Mks. 510, 511, 610) Tachometer No. 1 SBAC RS.570 cc 0.2154 7 50 Tachometer No. 2 SBAC RS.307 cc 0.2154 7 50 Power Turbine (Mks. 640, 641, 640A, 641A) Tachometer SBAC RS.307 c 0.216 7 50 * "c" - Clockwise "cc" - Counter clockwise facing engine pad. ** Speed - Times prime mover r.p.m. NOTE 5. Engine ratings are based on calibrated stand performance under the following conditions: Static sea level standard c onditions of 59°F and 29.92 in.Hg. Bristol Siddeley Air Intake Pt. No. WD.347- 35, and Exhaust unit Pt. No. HP.562 (item 2) Bristol Siddeley Starter bullet nose Pt. No: 8580 No external air bleed or accessory drive power for aircraft accessories. No anti-icing airflow. Additional performance parameters are contained in Bristol Siddeley Performance Brochure TC 602 (Mk.510), TC 607 (Mk.511), TC 603/2 (Mk.610), TC 604/3 (Mks.640, 641, 640A, 641A) Output shp ratings allow for gear box losses where applicable. E1EU Page 4 NOTE 6. Maximum permissible air bleed extraction is 6.3% of no-bleed mass flow, over whole range of Gas Generator r.p.m. subject to limiting power Turbine Inlet Temperature not being exceeded. NOTE 7. Power Turbine Normal Operating Range. The nominal power turbine operating speed is 19300 r.p.m. (Mks.510, 511, 610) and 19500 r.p.m. (Mks.640, 641, 640A, 641A). The operating range must not exceed the following limits: Power On Model Max. for Autorotation Minimum Maximum Mk. 510 21,000 17,700 19,700 Mk. 511 21,000 17,800 19,700 Mk. 610 21,000 17,800 20,100 Mks. 640,641,640A,641A 21,000 17,500 19,500 NOTE 8. Main Reduction Gearbox Output Sh aft Torque Limits (Mks. 510, 511, 610) Takeoff 11,160 in.lb. Max. continuous 10,200 in.lb. Max. overtorque 11,520 in.lb. Power Turbine Shaft Torque Limits (Mks. 640, 641, 640A, 641A) No limits provided that all other operating limitations are not exceeded. NOTE 9. To be eligible for use in certificated aircraft, the e ngine installation must include an accurate engine output torque measuring device or an acceptable alternate means of determining engine power. NOTE 10. These engines meet FAA requireme nts for operation in icing conditions, for adequate turbine disc integrity and rotor blade containment and do not require airframe-mounted armouring. NOTE 11. Maximum permi ssible overspeeds are: Gas Generator, (Mks. 510, 511) 27,100 r.p.m. for 20 seconds (Mks. 610, 640, 641, 640A, 641A) 27,550 r.p.m. for 20 seconds Power Turbine, (Mks. 510, 511, 610) 21,650 r.p.m. for 20 seconds (Mks. 640, 641, 640A, 641A) 23,100 r.p.m. for 20 seconds When either of these limits is exceeded, the engine must be disassembled for inspection. NOTE 12. Below 59°F the sea level static maximum power limits for the H.1200 engine will increase as follows: To 1328 PT.SHP maximum at 39°F for take-off, to 1207 PT.SHP maximum at 19°F for maximum continuous. Refer to B.S.E. Performance Brochures TC.603/2 and TC.604/3 for variations in power between standard day and ambi ent temperatures listed above. These maximum power limits of 1328 PT.SHP for takeoff and 1207 PT.SHP for maximum continuous are also authorized for use at any ambient temperat ure for engines whose individual characteristics permit higher than normal powers to be developed without exceeding operating limits. 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 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. ``` ## 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.