TCDS E44NE

* PAGE 1 2 3 4 REV. 5 5 5 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES IF ANY, ARE BLACK-LINED IN THE LEFT HAND MARGIN U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E44NE TCDS NUMBER E44NE REVISION: 5* DATE: February 1, 2008 CFE COMPANY MODELS: CFE738-1-1B Engines of models described herein conforming with this data sheet (which is a part of Type Certificate Number E44NE) 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: CFE COMPANY 111 South 34th Street Phoenix, AZ 85034 1. MODELS CFE738-1-1B TYPE Turbofan, Single Stage Fa n, Five Stage Axial Compressor, Single Stage Centrifugal Compressor, Annular Combustion Chamber, Two Stage High Pressure Turbine, Three Stage Low Pressure Turbine RATINGS (See NOTE 5) Sea Level Static Thrust, lb Maximum Takeoff (5 min.) (See NOTES 12, 16 & 17) Normal Takeoff (5 min.) (See NOTES 12, 16 & 17) Maximum Continuous (See NOTE 12) Rating ambient temperature Maximum Takeoff Normal Takeoff Maximum Continuous FUEL CONTROL FUEL OIL 5937 5918 5613 100oF (37oC) 86oF (30oC) 86oF (30oC) Fuel control and power management are controlled by a Full Authority Digital Electronic Control (FADEC) computer based system. The hardware and software configurations of this system and the associated engine fuel pump and hydromechanical unit are controlled by an approved engine equipment list for each specific engine model and aircraft application. Fuel conforming to General Electric Fuel Specification No. D50TF2, or current revision. See CFE738 Engine Installation Manual IM-7550 for specific fuels approved per the subject specifications. No. 3 Jet Fuel per GB6537-94 and No. 3A Jet Fuel per GB6537-05 is approved and conforms to the latest revision of General Electric Company jet fuel specification No. D50TF2 Oil conforming to General Electric Specification No. D50TF1, or Honeywell International, Inc oil specification EMS53110, current revision. See CFE738 Engine Installation Manual IM-7550 for specific oils approved per the subject specifications. E44NE -2 - I. MODELS (cont.) CFE738-1-1B PRINCIPAL DIMENSIONS The Principal Dimensions are lis ted on the approved Installation Drawing for each engine model. WEIGHT (dry maximum), pounds 1325 pounds (See NOTE 14) CENTER OF GRAVITY LOCATION, (in) The Cent er of Gravity is listed on the approved Installation Drawing for each engine model. IGNITION SYSTEM The ignition system is a dual-channel, continuous duty, capacitive discharge unit with independent circuits to each ignitor plug. The authorized ignition system components are controlled by the approved engine equipment list. CERTIFICATION BASIS (See NOTE 13) FAR 33, effective February 1, 1965, as amended by 33-1 through 33-14, dated August 10, 1990. Type Certificate Model Date of Application No. E44NE Issued CFE738-1-1B March 16, 1990 December 17, 1993 PRODUCTION BASIS Production Cer tificate No.108 issued January 13, 1961, and No. 413 issued March 4, 1965, under license from CFE Company, Phoenix, AZ. NOTES NOTE 1. Maximum permissible engine operating sp eeds for the engine rotors are as follows: CFE738-1-1B Low pressure rotor (N1), rpm Maximum Takeoff/Normal Takeoff 9,400 Maximum continuous 9,400 High pressure rotor (N2), rpm Maximum Takeoff/Normal Takeoff 28,000 Maximum continuous 27,715 NOTE 2. Maximum permissible temperatures are as follows: Interturbine temperature (T4.5), oF(oC) Maximum Takeoff (5 min.) 1634 oF (890oC) Normal Takeoff (5 min.) 1587 oF (864oC) Maximum Continuous 1582 oF (861oC) Oil inlet temperature, oF(oC) Continuous operation: 280 oF (138oC) Transient operation (3 min.): 280 oF (138oC) - 311oF (155oC) Fuel inlet temperature (at engine fuel pump inlet), oF(oC): 135 oF (57oC) E44NE -3 - NOTE 3. Fuel and Oil Pressure Limits Fuel Pump Inlet Pressure: Minimum: 5 PSI above true vapor pressure Maximum: 50 PSIG Oil Pressure: Minimum (idle): 30 PSIG Normal Operating Range: 60-85 PSIG Transient (3 min): 85-100 PSIG NOTE 4. ACCESSORY DRIVE PROVISIONS Accessory Drive Pad Type Speed Ratio (3) Rotation Facing Pad Maximum Torque (in-lb) Static Continuous Overload (2) Maximum Accessory Weight (lbs) Overhung Moment Max (lb-in) Alternator (D1) AS468B- AV1 Mod (1) 0.4418 CCW 1700 218 327 40 200 Alternator (D2) AS468B- AV1 Mod (1) 0.3666 CCW 1700 263 394 40 200 Starter (D3) AS468B- AV1 Mod (1) 0.5868 CCW 3900 1764( 5) 2712( 5) 25 150 Hydraulic Pump (D4) AS961B-1 Mod (1) 0.3082 CCW 600 210 315 10 30 Optional Hyd Pump (D5) AS961B-1 Mod(1) 0.3666 CCW 1700 263 394 40 200 NOTES: (1) Refer to the application pad definition on th e Installation Drawing for detailed information. (2) 5 minutes per each 4 hour period. (3) The accessory gearbox is driven from the High Pressure spool. (4) The engine Installation Manual lists the maximum combined simultaneous horsepower extraction for the alternator and hydraulic pump drives. (5) Limited to starts. NOTE 5. Engine ratings are based on calibrated test stand performance under the following conditions: Static sea level standard conditions of 59øF and 29.92 inches Hg. No aircraft accessory loads or air extraction. No anti-icing; no inlet distortion; no inlet screen losses; and 100% ram recovery. Inlet and exhaust system as defined in the engine Installation Manual IM-7550. Specified fuel having an average lower heating value of 18,400 BTU/lb; specified lube oil. E44NE -4 - NOTE 6. Maximum Compressor Bleed Air Extraction: P e r c e n t o f Core Airflow Low Pressure Bleed 8.0 High Pressure Bleed 5.5 Total LP and HP Bleed 12.0 NOTE 7. These engine models meet FAA requirements for operation in icing conditions within the envelope defined in FAR 25, Appendix C when installed and operated in accordance with approved data and instructions. NOTE 8. The maximum permissible inlet distortion is defined in the Engine Installation Manual IM-7550. NOTE 9. Life limits, established for critical rotating co mponents, are published in the approved engine Light Maintenance Manual, Report Number 72-06-03, Airworthiness Limitations Section. NOTE 10. Recommended engine inspection intervals are published in the approved engine Light Maintenance Manual, Report Number 72-06-03. NOTE 11. The operating temperature limits for specified components and accessories defined in the Engine Installation Manual IM-7550 must be observed when operating the installed engine. NOTE 12. Sea level static minimum rated thrust varies lin early between ambient temperature points shown below, but is flat rated below 59oF (15oC). SLS/59 oF(15oC) SLS/86 oF(30oC) SLS/100 oF(37oC) Maximum Takeoff 5888 5918 5937 Normal Takeoff 5888 5918 5454 Maximum Continuous 5613 5613 N/A NOTE 13. The engine model meets the requirements of FAR Part 34, original effective September 10, 1990. NOTE 14. The engine weight includes all components of the basic engine as defined by the approved engine equipment list. Components that are certified as part of the aircraft under FAR Part 25 and other optional equipment which are mounted on the engine are not included in the basic engine weight. NOTE 15. Engine Installation Manual IM-7550 and Oper ating Instructions IM-8007 contain additional FAA approved engine data. NOTE 16. The CFE738-1-1B engine normal takeoff intertur bine temperature (T4.5) limit has been established to assure that a fully degraded engine at the normal takeoff rating will achieve the maximum takeoff (APR) rated thrust without exceeding the maximum takeoff T4.5 limit. NOTE 17. The time limit at the normal takeoff rating is five minutes and shall include any time accumulated above the normal takeoff rating. NOTE 18. The CFE738-1 engine model was removed from T ype Certificate E44NE at the request of the type certificate holder. No CFE738-1 engine models are in existence. NOTE 19. Criteria pertaining to the dispatch and maintenan ce requirements for engine control systems are specified in CFE Report No. CFE1229(33)-4, which defines the various configurations and maximum operating intervals. ---END---