# TCDS E-287: Curtiss-Wright/Marquette Inc. - Type: Type certificate data sheet - Status: Current - Holder: Curtiss-Wright/Marquette Inc. - Revision: 7 - Revised: January 27, 2012 - Product: Engine - Data sheet PDF: https://openairdocs.org/files/sha256/8a/cb/8acb4e32151bf1665cfea33e7225bb58b8f5a7a099618ed3cd79a148ee8e9bca - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/7DD2A5254C2166DC86257992006C242B.0001 - Page: https://openairdocs.org/tcds/E-287 ## Models (7) As the data sheet lists them. - Double Row Turbo Cyclone 988TC18EA3 - Double Row Turbo Cyclone 988TC18EA1 - Double Row Turbo Cyclone 988TC18EA5 - Double Row Turbo Cyclone 988TC18EA6 - Double Row Turbo Cyclone 988TC18EA2 - Double Row Turbo Cyclone 988TC18EA4 - Double Row Turbo Cyclone 981TC18EA1 ## 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 Rev. No. 7 7 7 FEDERAL AVIATION AGENCY E-287 Revision 7 WRIGHT Double Row Turbo Cyclone 981TC18EA1 988TC18EA1,2,3,4,5,6 January 27, 2012 TYPE CERTIFICATE DATA SHEET NO. E-287 Engines of models described herein conforming with this data sheet (which is a part of type certificate No. E-287) 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. Manufacturer Curtiss-Wright/Marquette, Inc. Fountain Inn, South Carolina Model Double Row Turbo Cyclone 981TC18EA1 988TC18EA1, EA3 EA4, EA6 988TC18EA2, EA5 Type 18RA with 3 Blow-down, exhaust-driven turbines Reduction gear ratio 16:7 Turbo drive ratio 6.52:1 - - - - - - - - Rating (with low impeller gear ratio) 6.46:1 - - - - Max. continuous, hp, rpm, in.Hg. at: Critical pressure altitude (ft.) Sea level pressure altitude 2920-2650-49.5-4800 2860-2650-51.0-S.L. - - - - - - - - Takeoff (5 min.), hp, rpm, in.Hg. at: Critical pressure altitude (ft.) Sea level pressure altitude 3400-2900-56.0-4000 3400-2900-58.5-S.L. - - - - - - - - (with anti-detonant injection) Takeoff (5 min.), hp, rpm, in.Hg. at: Critical pressure altitude (ft.) Sea level pressure altitude 3700-2900-58.0-3200 3700-2900-58.5-S.L. — — — — (with high impeller gear ratio, dry) 8.67:1 - - - - Max. continuous, hp, rpm, in.Hg. at: Critical pressure altitude (ft.) Low critical pressure altitude (ft.) 2450-2600-47.0-16,400 2415-2600-48.5-10,800 - - - - - - - - Takeoff (5 min.), hp, rpm, in.Hg. at: Critical pressure altitude (ft.) Low critical pressure altitude (ft.) 2550-2600-49.0-15,200 2535-2600-49.5-13,300 - - - - - - - - Fuel (minimum grade aviation gasoline) 115/145 - - - - See Note 8. Lubricating oil MIL-L-6082, WAD Spec. 5815 or 5818 - - - - Bore and stroke, in. 6.125 X 6.312 - - - - Displacement, cu. in. 3350 - - - - Compression ratio 6.70:1 - - - - Weight (dry), lbs. 3670 3645 (EA1, 3) 3745 (EA2) C.G. location (dry) Fwd. of mounting flange centerline, in. Left of vertical centerline, viewed from rear, in. Off propeller shaft, in. 18.22 0.014 0.133 above 3675 (EA4, 6) - - - - - - 3775 (EA5) 18.54 0.021 0.193 below Propeller shaft, SAFE no. 60 - - - - Fuel injection model Bendix Stromberg PR-58-S2 master control with two Direct injection pumps - - - - Ignition, Dual Timing, BTC Scintilla DLN-9 magneto 25 (30 in cruise) - - - - - - - - Model Double Row Turbo Cyclone 981TC18EA1 98TC18EA1, EA3 EA4, EA6 988TC18EA2, EA5 Spark plugs See Note 9. - - - - NOTES 1 through 10 1 through 9 1 through 9 "- -" indicates "same as preceding model." "—" indicatoes "does not apply." Certification basis Type Certificate No. 287 Production basis Production certificate No. 8 NOTE 1. Maximum permissible temperatures are as follows: Head (Well Type Thermocouple) Barrel Oil Inlet 475  (500 for T.O. only) 350  220  NOTE 2. Fuel and oil pressure lmits: Oil pressure (psi) 70  5. Fuel pressure (psi) 25  2 NOTE 3. The following accessory drives are provided: Maximum Torque (in. lbs.) Maximum Bending Accessory Rotation* Speed** Continuous Static Moment (in. lbs.) Starter C 1.000 - 36000 350 Generator and accessory (2) C 3.110 1500 6600 400 Fuel pump (2) CC 1.000 25 450 15 Hydraulic pump (RH) C 1.400 600 2700 350 Hydraulic pump (LH) C 1.400 250 1650 75 Vacuum pump C 1.400 250 1650 75 Tachometer (2) 1C 0.500 22 50 15 1CC Propeller governor C 0.857 125 825 30 *"C" - Clockwise viewing drive pad "CC" - Counter clockwise **Speed - Times crankshaft rpm NOTE 4. These engines incorporate torquemeters, provi sions for crankcase mounting and double-acting hydraulic propeller provisions. NOTE 5. The ratings of these engines are based on standa rd conditions of temperature and barometric pressure (60 F and 29.92 in.Hg. at sea level) and 80% relative humidity. If corrected to dry standard air conditions, the rated powers would be increased appr oximately 2.5% at sea level to 0.4% at 15,000 ft. for equal manifold pressure settings. NOTE 6. These engines incorporate 3 bl ow-down turbines for exhaust gas power recovery. To insure against secondary damage being caused by a turbine blad e failure, it is required that each turbine wheel be provided with an approved type of guard prior to use in certificated aircraft. These guards should be capable of at least cushioning the energy effects of a failed blade. NOTE 7. The model 988TC18EA1 is sim ilar to the 988TC18EA3 model, except for installation feature differences. The 988TC18EA2 is similar to the 988T C18EA1 except for reduction gear ratio. The models 988TC18EA4, 5 and 6 are similar to models 988TC18EA1, 2 and 3 respectively except for parts variations which permit increased cruise power ratings. 3 E-287 NOTE 8. The 988TC18EA1, 2, 3, 4, 5, and 6 engines are e ligible for use with grade 100/130 at the following ratings for all operations include cruise: With low impeller gear ratio: Max. continuous, hp, rpm, in.Hg. at: Critical pressure altitude (ft.) Sea level pressure altitude 2450-2600-41.5-9400 2380-2600-44.0-S.L. Takeoff (5 min.) hp, rpm, in.Hg. at: Critical pressure altitude (ft.) Sea level pressure altitude 2950-2900-48.0-8500 2880-2900-53.0-S.L. With high impeller gear ratio: Operation with grade 100/130 fuel not permitted. NOTE 9. The following spark plugs are approved on these engines: AC 275, 286A, 288, 298 Champion R103, RHB27P, R HA29E, RHA29N, RHB29E, RHB29N Lodge RS35R (except EA4, 5 and 6) NOTE 10. The wet low ratio takeoff rating of the 981TC18EA1 engine is based on the use of fuel derichment and water-alcohol injection at the rate of 18-1/4 pounds per minute at 26 p.s.i. at the control valve. The water injection fluid should comply with AMS-3006 Type 1 which specifies: Methyl alcohol 48-52% by volume Water 48-52% by volume ....END..... ``` ## ADs (10, in force first) - [AD 60-08-05](https://openairdocs.org/ad/60-08-05): Cooling Shield to Wheel Lip Clearance · Curtiss-Wright/Marquette Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91), Double Row Turbo Cyclone 972TC18DA2, Double Row Turbo Cyclone 972TC18DA3 and 8 more. Effective May 19, 1971 - [AD 56-20-06](https://openairdocs.org/ad/56-20-06): Gear Shafts · Curtiss-Wright/Marquette Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91), Double Row Turbo Cyclone 972TC18DA2, Double Row Turbo Cyclone 972TC18DA3 and 9 more - [AD 57-06-04](https://openairdocs.org/ad/57-06-04): Engine Front Section · Curtiss-Wright/Marquette Double Row Cyclone 956C18CA1, Double Row Cyclone 975C18CB1, Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91) and 10 more - [AD 57-08-07](https://openairdocs.org/ad/57-08-07): Impeller Drive Gear Assemblies · Curtiss-Wright/Marquette Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91), Double Row Turbo Cyclone 972TC18DA2, Double Row Turbo Cyclone 972TC18DA3 and 8 more - [AD 57-24-01](https://openairdocs.org/ad/57-24-01): Impeller Drive Gear Assemblies · Curtiss-Wright/Marquette Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91), Double Row Turbo Cyclone 972TC18DA2, Double Row Turbo Cyclone 972TC18DA3 and 8 more - [AD 58-13-05](https://openairdocs.org/ad/58-13-05): Piston Compression Ring · Curtiss-Wright/Marquette Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91), Double Row Turbo Cyclone 972TC18DA2, Double Row Turbo Cyclone 972TC18DA3 and 8 more - [AD 58-18-01](https://openairdocs.org/ad/58-18-01): Governor · Curtiss-Wright/Marquette Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91), Double Row Turbo Cyclone 972TC18DA2, Double Row Turbo Cyclone 972TC18DA3 and 9 more - [AD 59-10-05](https://openairdocs.org/ad/59-10-05): Governors. · Curtiss-Wright/Marquette Double Row Turbo Cyclone 981TC18EA1, Double Row Turbo Cyclone 988TC18EA1, Double Row Turbo Cyclone 988TC18EA2 and 5 more - [AD 59-17-01](https://openairdocs.org/ad/59-17-01): Propeller Shaft · Curtiss-Wright/Marquette Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91), Double Row Turbo Cyclone 972TC18DA2, Double Row Turbo Cyclone 972TC18DA3 and 8 more - [AD 60-03-10](https://openairdocs.org/ad/60-03-10): Oil Control Valve · Curtiss-Wright/Marquette Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91), Double Row Turbo Cyclone 972TC18DA2, Double Row Turbo Cyclone 972TC18DA3 and 8 more ## STCs approved under this data sheet (6) - [STC SE01966WI](https://openairdocs.org/stc/SE01966WI): Use of GAMI G100UL High Octane Unleaded Avgas in spark ignition piston aircraft engines. General Aviation Modifications Inc. - [STC SE204SO](https://openairdocs.org/stc/SE204SO): Rework of cylinder assembly.. Delta A & E Sales Co - [STC SE207SO](https://openairdocs.org/stc/SE207SO): Modification of PRT cooling cap. (CYCLONE 972TC18DA1 Military R-3350 Series). Delta A & E Sales Co - [STC SE2WE](https://openairdocs.org/stc/SE2WE): Cylinder and intercylinder cooling baffles.. Berry Frank R - [STC SEW-2](https://openairdocs.org/stc/SEW-2): Fabrication of engine exhaust system clamps M-7540, M-7541 and M-7544.. Exhaust Parts Inc - [STC SEW-4](https://openairdocs.org/stc/SEW-4): Exhaust system parts.. Exhaust Parts 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.