TCDS E00052EN

* PAGE 1 2 3 REV. 0 0 0 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00052EN TCDS NUMBER E00052EN REVISION: ORIGINAL DATE: DECEMBER 21, 1995 HAMILTON STANDARD MODELS: FV4000-2TC Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00052EN) 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 Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. TYPE CERTIFICATE (TC) HOLDER: Hamilton Standard Division United Technologies Corporation One Hamilton Road Windsor Locks, CT 06096-1010 1. MODELS FV4000-2TC TYPE An eight cylinder reciprocating engine configured in a V-8 block with a geared propeller drive system on the forward end and an accessory drive system on the aft end. The engine incorporates dual overhead camshafts, four valves per cylinder, a dual channel full authority digital engine control, and liquid cooling. RATINGS (U.S. Standard Atmosphere at Sea Level Pressure Altitude) Reduction Gear Ratio Max. Continuous and Takeoff HP Max. Continuous Engine RPM Max. Continuous Man. Pr. In. Hg. Critical Altitude - Ft. 0.3846:1 360 5200 43 18,000 FUEL (Aviation Gasoline) 100LL (Blue) LUBRICATING OIL (Engine and Turbocharger) Mobil -1 (SG/CD 5W-30) COOLANT 60% LLC/40% water (Toyota Antifreeze- LLC) BORE AND STROKE - in. 3.44x3.25 DISPLACEMENT, cu. in. 242 COMPRESSION RATIO 9.7:1 PROPELLER SHAFT Integral SAE No. 6 flange with six 1/2 inch bolt holes on a 4.75 inch diameter circle TCDS E00052EN PAGE 2 I. MODELS (cont.) FV4000-2TC IGNITION-Electronic Engine Control (EEC) Ignition, fuel injection, and wastegate are controlled by EEC300, EEC300 is a full authority digital engine control (FADEC). TIMING Variable, controlled by EEC300 SPARK PLUGS One per cylinder (eight cylinders) OIL SUMP CAPACITY, Qts. (Drain & Refill) 7.0 - full level horizontal, attitude range is 30o nose up and 17.5o nose down. PRINCIPAL DIMENSTIONS (in) Refer to HS dwg 817450 WEIGHT (lbs) (Dry, no oil and no coolant) Includes basic engine, reduction gearbox, turbochargers, intercoolers, throttle, PRCV, waste gate valve (WGV), WGV actuator, WGV control cable, scavenging pump, alternators, engine mount brackets, starter 520 CENTER OF GRAVITY LOCATIONS (in) Refer to HS dwg. 817450. CERTIFICATION BASIS Federal Aviation Regulations (FAR) Part 33, effective February 1, 1965, and Amendments 33-1 to 33-15, inclusive. TYPE CERTIFICATE E00052EN MODELS APPLICATION DATE ISSUED/AMENDED FV4000-2TC March 17, 1993 December 21, 1995 PRODUCTION BASIS Production Certificate No. TBD NOTES NOTE 1. MAXIMUM PERMISSIBLE TEMPERATURES: Engine Coolant 212oF Engine Oil 230oF Exhaust Gas Turbocharger Inlet 1562oF Temperature (T.I.T.) NOTE 2. FUEL & OIL PRESSURE LIMITS Pressure difference between fuel pressure regulator and intake manifold pressure 42-52 psi Engine Oil Pressure Limits Idle - 11 psig (minimum) Max 100 psig NOTE 3. The following accessory drive or mounting provisions are available: TCDS E00052EN PAGE 3 Accessory Direction of Rotation* Gear Ratio to Crankshaft Max Weight (lbs) Max Torque Continuous (in-lbs) Maximum Overhung Moment (in-lbs) Freon Compressor CW NA 15.5 94.6 40 Propeller Gov.** CCW .5:1 9.8 100 40 Accessory Drives (2)** CW .5:1 10.6 95.8 40 * "CW" - Clockwise and "CCW" - Counterclockwise (Viewing Engine Drive Pad) ** These drives shall be supplied with covers. NOTE 4. The Installation Manual for the FV4000-2TC Engine System contains the requirements for installation of the FV4000-2TC engine system. All limitations and requirements must be followed to ensure safety. NOTE 5. The Operation Manual for the FV4000-2TC Engine System contains the requirements for operating the FV4000-2TC engine system. All limitations and requirements must be followed to ensure safety. NOTE 6. Specified Fuel Consumption: - Rated max continuous and takeoff HP = .502 lbs/hp-hr. This is at 5200 rpm. - Maximum best economy cruise at 4400 rpm = .382 lbs/hp-hr. NOTE 7. Oil consumption = 2-3.4 oz/hr. This is an average value over 800 hours of operation. -----END-----