TCDS E-272

Page No. 1 2 3 Rev. No. 9 9 9 FEDERAL AVIATION AGENCY E-272 Revision 9 WRIGHT Double Row Turbo Cyclone 972TC18DA1 (Military R-3350-34, R-3350-91) 972TC18DA2 972TC18DA3 972TC18DA4 December 28, 1983 TYPE CERTIFICATE DATA SHEET NO. E-272 Engines of models described herein conforming with this data sheet (which is a part of type certificate No. E-272) and other aproved 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 972TC18DA1 (R-3350-34, -91), 972TC18DA2 972TC18DA3, 972TC18DA4 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 2650-2600-45.0-6500 2600-2600-47.5-S.L. 2750-2600-47.0-5800 2700-2600-49.0-S.L. Takeoff (5 min.), hp, rpm, in.Hg. at: Critical pressure altitude (ft.) Sea level pressure altitude 3250-2900-53.0-5000 3250-2900-56.5-S.L. 3250-2900-53.5-5500 3250-2900-56.5-S.L. (with high impeller gear ratio) 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 2405-2600-48.5-9550 - - 2405-2600-48.5-10,050 Takeoff (5 min.), hp, rpm, in.Hg. at: Critical pressure altitude (ft.) Low critical pressure altitude (ft.) 2550-2600-49.0-15,200 2535-2600-49.5-12,800 - - 2535-2600-49.5-13,300 Fuel (minimum grade aviation gasoline) 115/145 - - 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. 3550 - - C.G. location (dry) Fwd. of mounting flange centerline, in. Left of vertical centerline, viewed from rear, in. Above propeller shaft, in. 18.22 0.014 0.133 - - - - - - Propeller shaft, SAFE no. 60 - - E-272 2 Model Double Row Turbo Cyclone 972TC18DA1 (R-3350-34, -91), 972TC18DA2 972TC18DA3, 972TC18DA4 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) - - - - Spark plugs See Note 10. - - NOTES 1,2,3,4,5,6,7,8,9,10 1,2,3,4,5,6,7,8,9,10 "- -" indicates "same as preceding model." Certification basis Type Certificate No. 272 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 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 C 1.400 600 2700 350 Vacuum pump (2) 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, provisions for crankcase mounting and double-acting hydraulic propeller provisions. NOTE 5. The ratings of these engines are based on standard 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 approximately 2.5% at sea level to 0.4% at 15,000 ft. for equal manifold pressure settings. NOTE 6. These engines incorporate 3 blow-down turbines for exhaust gas power recovery. To insure against secondary damage being caused by a turbine blade 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 military R-3350-34 and R-3350-91 engines are identifical to the 972TC18DA1 and are eligible for use in certificated aircraft; however, when used civilly the engine name plate should be revised to include the corresponding civil model designations and type certificate no. 3 E-272 NOTE 8. The model 972TC18DA2 and DA4 engines are similar to the 972TC18DA1 and DA3 models, respectively, except for installation feature differences. NOTE 9. These engines are eligible for use with grade 100/130 fuel at the following ratings for all operations including cruise: 972TC18DA1 972TC18DA3 972TC18DA2 972TC18DA4 With low impeller gear ratio: Maximum continuous, hp, rpm, in. Hg. at: Critical pressure altitude (ft.) 2450-2600-41.0-9100 2450-2600-41.5-9400 Sea level pressure altitude 2380-2600-43.5-S.L. 2380-2600-44.0-S.L. Takeoff (5 min.), hp, rpm, in.Hg., at: Critical pressure altitude (ft.) 2950-2900-47.5-8100 2950-2900-48.0-8500 Sea level pressure altitude 2880-2900-53.0-S.L. 2880-2900-53.0-S.L. With high impeller gear ratio: Operation with grade 100/130 fuel not permitted. NOTE 10. The following spark plugs are approved on these engines: AC 275, 286A, 288, 298 Champion R103, RHB27P, RHA29E, RHA29N, RHB29E, RHB29N Lodge RS35R .....END....