TCDS E3NE

* PAGE 1 2 3 4 5 6 7 8 9 10 REV. 16 14 11 11 16 16 11 11 16 16 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE SHEET E3NE TCDS NUMBER E3NE REVISION: 16 DATE: July 25, 2019 PRATT & WHITNEY MODELS: JT9D-59A JT9D-70A JT9D-7Q JT9D-7Q3 JT9D-7R4D JT9D-7R4D1 JT9D-7R4E JT9D-7R4E1 JT9D-7R4G2 JT9D-7R4H1 JT9D-7R4E4 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E3NE) 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: Pratt & Whitney United Technologies Corporation East Hartford, Connecticut 06108 I. MODELS JT9D-59A JT9D-70A JT9D-7Q TYPE Turbofan, dual axial 16 stage compressor, annular combustion chamber, and 6 stage turbine. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb. Takeoff static thrust at sea level, lb. Dry (5 min.) (See NOTE 13) 44,770 51,720 44,290 51,140 44,920 51,900 COMPONENTS Fuel Control Fuel Pump High Compressor Stator Vane Control/ 3.0 Bleed Control or Engine Vane and Modulating Bleed Control Start Bleed Control (3.5 bleed control) Electronic Engine Control Ham. Std. JFC68-6 TRW 385200 Ham. Std./ EVC 3-5/ 674977 or Ham. Std. GTA9-1 PWA P/N 773456 --- - - - - - - - - - - --- - - TRW 386900 - - - - - - --- FUEL See NOTE 10 - - - - OIL See NOTE 11 - - - - TCDS E3NE PAGE 2 I. MODELS (CONT.) JT9D-59A JT9D-70A JT9D-7Q PRINCIPAL DIMENSIONS Maximum length, in. (including spinner) Width, in. Weight (dry), lb. ( includes basic engine with all essential accessories; with fuel heater, oil tank, fuel oil cooler, and CSD fuel oil cooler; but excluding starter, exhaust nozzle and power source for the ignition systems) Center of gravity, in. Forward of engine reference plane Below engine center line IGNITION Exciters 154.256 97.030 9,140 5.2+1.0 3.3+0.5 Unison 5005907-01 (two) - - - - 9,155 - - - - - - - - - - 9,295 2.5+1.0 1.4+0.5 - - Igniters (two each) Champion 709520 - - - - II. MODELS JT9D-7Q3 JT9D-7R4D JT9D-7R4D1 JT9D-7R4E TYPE Turbofan, dual axial 16 stage compressor, annular combustion chamber, and 6 stage turbine. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb. Takeoff static thrust at sea level, lb. Dry (5 min.) (See NOTE 13) 44,920 51,900 45,800 48,000 45,800 48,000 47,500 50,000 COMPONENTS Fuel Control Fuel Pump High Compressor Stator Vane Control/ 3.0 Bleed Control or Engine Vane and Modulating Bleed Control Start Bleed Control (3.5 bleed control) Electronic Engine Control (See NOTE 19) Ham. Std. JFC68-6 TRW 386900 Ham. Std./ EVC 3-5/ 674977 or Ham. Std. GTA9-1 PWA P/N 773456 --- Ham. Std. JFC68-7 TRW 706800 - - or GTA9-3 793396 Ham. Std. 780170-6 780170-5 780170-2 780170-8 Ham. Std. JFC68-10 - - - - - - - - Ham. Std. 769370-3 Ham. Std. JFC68-7 - - - - - - 769486 Ham. Std. 780170-6 780170-8 FUEL NOZZLES --- --- --- --- EEC PROGRAMMING PLUG (PWA P/N) --- 795034 795354 795035 FUEL See NOTE 10 - - - - - - OIL See NOTE 11 - - - - - - TCDS E3NE PAGE 3 II. MODELS (CONT.) JT9D-7Q3 JT9D-7R4D JT9D-7R4D1 JT9D-7R4E PRINCIPAL DIMENSIONS Maximum length in. (including spinner) Width, in. Weight (dry), lb. (includes basic engine with all essential accessories; with fuel heater, oil tank, fuel oil cooler, and CSD fuel oil cooler; but excluding starter, exhaust nozzle and power source for the ignition systems) Center of gravity, in. Forward of engine reference plane Below engine center line IGNITION Exciters 154.256 97.03 9,295 2.5+1.0 1.4+0.5 Simmonds Precision P/N 43925 - - 96.00 8,935 3.3+1.0 - - Simmonds Precision RH P/N 43925 LH P/N 44933 - - - - 8,915 - - - - - - - - - - - - - - - - - - Igniters (two each) Champion AA134S-1 or AC S611809 - - - - - - III. MODELS JT9D-7R4E1 JT9D-7R4G2 JT9D-7R4H1 JT9D-7R4E4 TYPE Turbofan, dual axial 16 stage compressor, annular combustion chamber, and 6 stage turbine. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb. Takeoff static thrust at sea level, lb. Dry (5 min.) (See NOTE 13) 47,500 50,000 50,200 54,750 50,000 56,000 47,500 50,000 COMPONENTS Fuel Control Fuel Pump High Compressor Stator Vane Control/ 3.0 Bleed Control or Engine Vane and Modulating Bleed Control Start Bleed Control (3.5 bleed control) Electronic Engine Control Ham. Std. JFC68-10 TRW 706800 Ham. Std. /EVC 3-5/ 674977 or GTA9-3 793396 (See NOTE 20) - - JFC68-8 - - - - - - 769486 --- - - JFC68-10 - - - - - - 793396 Ham. Std. 787240-1 - - JFC68-7 - - - - - - 769486 Ham. Std. 780170-8 FUEL NOZZLES --- --- --- (See NOTE 18) EEC PROGRAMMING PLUG (PWA P/N) 795035 --- 795036 798873 FUEL See NOTE 10 - - - - - - OIL See NOTE 11 - - - - - - TCDS E3NE PAGE 4 III MODELS (CONT.) JT9D-7R4E1 JT9D-7R4G2 JT9D-7R4H1 JT9D-7R4E4 PRINCIPAL DIMENSIONS Maximum length in. (including spinner) Width, in. Weight (dry), lb. (includes basic engine with all essential accessories; with fuel heater, oil tank, fuel oil cooler, and CSD fuel oil cooler; but excluding starter, exhaust nozzle and power source for the ignition systems) Center of gravity, in. Forward of engine reference plane Below engine center line IGNITION Exciters 154.295 96.00 8,935 3.3+1.0 1.4+0.5 Simmonds Precision RH P/N 43925 LH P/N 44933 - - - - 9,170 - - - - - - - - - - 8,915 - - - - - - - - - - 8,935 - - - - - - Igniters (two each) Champion AA134S-1 or AC S611809 - - - - - - CERTIFICATION BASIS FAR 33 effective February 1, 1965, as amended by 33-1, 33-2, 33-3, and 33-4, and Special Condition No. 33-8-EA-3. Type Certificate No. E3NE, issued December 12, 1974 (JT9D-59A, 70, 70A); and subsequent revisions issued March 19, 1976 (JT9D-59B, 70B); issued October 31, 1978 (JT9D-7Q, 7Q1); issued October 22, 1979 (JT9D-7Q3); issued June 4, 1980 (JT9D-59D, 70D, 7Q2); issued November 25, 1980 (JT9D-7R4A, 7R4D); issued April 1, 1981 (JT9D-7R4D1, 7R4E1); issued July 23, 1982 (JT9D-7R4G2, 7R4H1, 7R4H2); issued March 29, 1985 (JT9D-7R4E4). Dates of Application for Type Certificate: May 2, 1973 (JT9D-70); September 4, 1974 (JT9D-59A); October 17, 1974 (JT9D-70A); February 20, 1976 (JT9D-59B, 70B); October 28, 1977 (JT9D-7Q); June 15, 1978 (JT9D-7Q1); July 6, 1978 (JT9D-59D, 70D); August 14, 1978 (JT9D-7Q2); October 10, 1979 (JT9D-7Q3); February 14, 1979 (JT9D-7R4A, 7R4D); December 22, 1980 (JT9D-7R4D1); February 10, 1981 (JT9D-7R4E1); February 14, 1979 (JT9D-7R4G2, 7R4H1, 7R4H2); and October 11, 1984 (JT9D-7R4E4). PRODUCTION BASIS Production Certificate Number 2 TCDS E3NE PAGE 5 NOTES NOTE 1. Maximum permissible engine operating speeds for the engine rotors are as follows: JT9D- JT9D- JT9D- JT9D- JT9D- JT9D-59A/70A 7Q 7Q3 7R4D+ 7R4D1 7R4E1 Low pressure rotor (N1), rpm 3780 3888 3960 3770 3810 3810 High pressure rotor (N2), rpm 8011 8000 8000 8000 8000 8000 JT9D- JT9D- JT9D- JT9D- 7R4E+ 7R4G2 7R4H1 7R4E4 Low pressure rotor (N1), rpm 3770 3825 3810 3810 High pressure rotor (N2), rpm 8000 8080 8080 8080 For inadvertent exceedances of certified overspeed limits, see Chapter 72-00-00 of the appropriate maintenance manual. +Engines converted from JT9D-7R4E4 per Service Bulletin JT9D-7R4-72-331 or Special Instruction 34F-87 (EC86EA123) and operated to either JT9D-7R4D or JT9D-7R4E ratings will have the engine model identifier of “(DM)” or “(EM)” after the engine model name and will have maximum permissible rotor speeds as follows: Low Pressure Rotor (N1), rpm 3810 High Pressure Rotor (N2), rpm 8080 NOTE 2. Maximum permissible temperatures are as follows: Turbine gas temperature (Tt7) total temperature immediately downstream from the low pressure turbine discharge. JT9D-59A/7Q3 JT9D-70A/7Q Takeoff (5 minutes) (685˚C) 1265˚F (685˚C) 1265˚F Maximum continuous (650˚C) 1202˚F (650˚C) 1202˚F Maximum accleration (685˚C) 1265˚F (685˚C) 1265˚F Ground Starting (505˚C) 941˚F - - Inflight Starting++ (505˚C) 941˚F - - Oil Inlet (135˚C) 275˚F (continuous operation) - - (163˚C) 325˚F (transient operation - - limited to 20 minutes) JT9D- JT9D- JT9D- JT9D-7R4D+ 7R4D1 7R4E1 7R4E+ Takeoff (5 minutes) (625˚C) 1157˚F (625˚C) 1157˚F (635˚C) 1175˚F - - Maximum continuous (600˚C) 1112˚F (600˚C) 1112˚F (610˚C) 1130˚F - - Maximum accleration (625˚C) 1157˚F (625˚C) 1157˚F (635˚C) 1175˚F - - Ground Starting (535˚C) 995˚F (535˚C) 995˚F - - - - - - Inflight Starting++ (625˚C) 1157˚F (625˚C) 1157˚F (635˚C) 1175˚F - - Oil Inlet Maximum oil inlet temperature is not to exceed 275˚F (135˚C). - - During idle descent, a 325˚F (163˚C) limit is permissible for up to 20 minutes. ++ If during an inflight start, the normal ground starting EGT is exceeded, maximum EGT and duration must be recorded for maintenance action. TCDS E3NE PAGE 6 NOTE 2. (Continued) Maximum permissible temperatures are as follows: JT9D- JT9D- JT9D- 7R4G2 7R4H1 7R4E4 Takeoff (5 minutes) (685˚C) 1265˚F (680˚C) 1256˚F - - Maximum continuous (620˚C) 1148˚F (635˚C) 1175˚F - - Maximum accleration (660˚C) 1220˚F (675˚C) 1247˚F - - Ground Starting (535˚C) 995˚F - - - - - - Inflight Starting++ (535˚C) 995˚F (680˚C) 1256˚F - - Oil Inlet Maximum oil inlet temperature is not to exceed 275˚F (135˚C). - - During idle descent, a 325˚F (163˚C) limit is permissible for up to 20 minutes. For inadvertent exceedances fo certified temperature limits see Chapter 72-00-00 of the appropriate maintenance manual. External engine limiting temperatures for specific components are specified in the engine installation and operation manual. +Engines converted from -7R4E4 per Service Bulletin JT9D-7R4-72-331 or Special Instruction 34F-87 (EC86EA123) and operated to either -7R4D or -7R4E ratings will have the engine model identifier of “(DM)” or “(EM)” after the engine model name and will have an EGT limit as follows: o Takeoff (680˚C) 1256˚F o Max Cont. (635˚C) 1175˚F o Max Accel (675˚C) 1247˚F ++If during an inflight start, the normal ground starting EGT is exceeded, maximum EGT and duration must be recorded for maintenance action. NOTE 3. Fuel and oil pressures are as follows: Fuel pressure: At inlet to engine system pump, not less than 5 psi above the true vapor pressure of the fuel and not greater than 70 psig with a vapor/liquid ratio of zero. Oil pressure: Minimum 35 psig (normal range 40-60 psig) NOTE: During cold weather starting, oil pressure in excess of 60 psig may be evidenced until oil viscosities are reduced by increasing oil temperature. Engine operation is limited to idle power when oil pressure is in excess of 60 psig during cold weather starts. NOTE 4. Maximum permissible air bleed extraction is as follows: JT9D-59A/7Q JT9D-7R4D/7R4D1/7R4E1 70A/7Q3 7R4E/7R4G2/7R4H1/7R4E4 Percent of Primary Engine Airflow Percent of Primary Engine Airflow Normal Bleed Maximum Bleed Normal Bleed Maximum Bleed High compressor bleed a. Idle to 40% max cont. 10% 13% 9% 9% b. 40% max cont. to takeoff* 5% 6.5% 5% 5% *5% is the maximum allowable from the 8th stage in this thrust range. The 6.5% listed is allowable from the15th stage alone or from a combination of 8th and 15th stage bleeds. TCDS E3NE PAGE 7 NOTE 5. Ratings, with the exception of the -7R4 models, are based on static test stand operation under the following conditions: Compressor inlet air at 59ºF and 29.92 in. Hg. Engine air inlet, jet nozzle exhaust pipe, and fan exit nozzle per P&W Drawing P/N 758201(-59A); 760701 (-70A); 808801 (7Q and 7Q3). No aircraft accessory loads or air extraction. No anti-icing airflow. Turbine gas temperature limits and engine rotor speed limits not exceeded. Rating for -7R4 models are based on ideal nozzles. NOTE 6. The following accessory drive provisions are incorporated: JT9D-7Q/7Q3/59A/70A ________________________________________________________________________ Rotation (facing pad) Speed Ratio (C - Clockwise, CC - to Torque (in-lb) Overhang Drive Counter Clockwise) Turbine Shaft Continuous Static (in-lb) Starter CC 1.091:1 (a) (a) 500 Generator - - - - 1,575 Constant Speed CC 1.091:1 (b) 15,960 1,575 Drive Tachometer C .538:1 7 50 - Fluid Power CC .500:1 1,890 9,450 400 Pumps (2) CC .499:1 1,890 9,450 400 (a) 750 ft-lb engine starter drive shear section is designed to fail at a static torque of 1,400 - 1,610 ft-lb (b) Maximum allowable continuous torque values are equivalent to 210 horsepower at any engine speed at or above sea level ground idle. (c) "-" indicates "does not apply" JT9D-7R4D/7R4D1/7R4E1/7R4E/7R4G2/7R4H1/7R4E4 _______________________________________________________________________ Rotation (facing pad) Speed Ratio (C - Clockwise, CC - to Torque (in-lb) Overhang Drive Counter Clockwise) Turbine Shaft Continuous Static (in-lb) Starter CC 1.091:1 (a) (a) 500 Generator - - - - 1,575 Constant Speed CC 1.091:1 (b) 15,960 1,575 Drive Tachometer C .538:1 7 50 - Fluid Power CC .500:1 1,890 9,450 400 Pumps (2) CC .499:1 1,300 6,500 400 IDGS CC 1.121:1 12,620 2,000 (a) 910 ft-lb engine starter drive shear section is designed to fail at a static torque of 1,400 - 1,610 ft-lb (b) Maximum allowable continuous torque values are equivalent to 210 horsepower at any engine speed at or above sea level ground idle. (c) "-" indicates "does not apply" TCDS E3NE PAGE 8 NOTE 7. Power setting, power checks, and control of engine output in all operations are to be used based upon P&W engine charts referring to turbine discharge section gas pressure. Pressure probes are included in the engine assembly for this purpose. NOTE 8. For inflight operation during icing conditions, the minimum N1 rpm is 20% for JT9D-7R4 series engines. For JT9D- 59 series, 70 series, and 7Q series engines, maintain at least 50% N1 rpm above 10,000 feet and at least 45% N1 rpm below 10,000 feet. NOTE 9. This model engine meets Item 1 in Special Condition No. 33-8EA-3 in the uncowled configuration. NOTE 10. Fuels meeting the requirements of the latest applicable issue of Turbojet Engine Service Bulletin No. 2016, which includes other fuel information requirements of PW Specification No. 522, are acceptable for these engines. Approved fuel additives and allowable concentrations are also included in Service Bulletin No. 2016. NOTE 11. The following oils are eligible for these engines: Synthetic type conforming to P&W Specification No. 521C, or later revision. Approved brand oils listed in P&W Turbojet Engine Service Bulletin No. 238. NOTE 12. Certain engine parts are life limited. These limits are listed in the "FAA approved" time limits section of the P&W Engine Manuals P/N 754459 for the JT9D-59/70 series; P/N 777210 for the -7Q series; P/N 785058 for the -7R4D1, -7R4E1 and -7R4H1; P/N 785059 for the -7R4D, -7R4E and -7R4E4; P/N 789328 for the -7R4G2. TCDS E3NE PAGE 9 NOTE 13. JT9D Model Characteristics -59A Takeoff rating of 51,720 lb at and below 86ºF ambient temperature, sea level static. -70A Takeoff rating of 51,140 lb at and below 86ºF ambient temperature, sea level static. -7Q Internally the same as JT9D-50/-70 series engines, but externally configured to fit in Boeing 747-200 nacelle. Takeoff rating of 51,900 lb at and below 86ºF ambient temperature, sea level static. -7Q3 Basically the same as JT7D-7Q except for revised fan case for the increased maximum low rotor speed. -7R4D Bascially the same as JT9D-7 (see TCDS E20EA) except incorporates an improved fan, higher efficiency 4 stage LPC, single crystal first stage turbine blades, improved use of turbine cooling air and a supervisory Electronic Engine Control. Takeoff rating of 48,000 lb at and below 92ºF ambient temperature, sea level static. -7R4D1 Same as -7R4D except for external arrangement required for installation. -7R4E1 Same as -7R4D1 except takeoff rating of 50,000 lb at and below 92ºF ambient temperature, sea level static. -7R4E Same as -7R4D except takeoff rating of 50,000 lb at and below 92ºF ambient temperature, sea level static. -7R4G2 Same as -7R4D except incorporates an improved durability hot section including wide chord vanes. Takeoff rating 54,750 lb at and below 86ºF ambient temperature, sea level static. -7R4H1 Same as -7R4G2 except for external arrangement required for installation and also incorporates single crystal first and second stage turbine blades and single crystal second turbine vanes. Takeoff rating 56,000 lb at and below 86ºF ambient temperture, sea level static. -7R4E4 Same as -7R4E except incorporates burner and high turbine configuration of the -7R4H1. Takeoff rating of 50,000 lb at and below 114ºF ambient temperature, sea level static. The -7R4E4 if derated to the (EM) in accordance wuth P&W Special Instrcution 34F-87 will have takeoff rating of 50,000 lb. at and below 92ºF ambient temperature, sea level static; and have the engine model identifier of -7R4E4(EM) on the engine dataplate. The –7R4E4 if derated to the (DM) in accordance with P&W Special Instrcution 34F-87 will have takeoff rating of 48,000 lb. at and below 92ºF ambient temperature, sea level static; and have the engine model identifier of -7R4E4(DM) on the engine dataplate. TCDS E3NE PAGE 10 NOTE 14. All JT9D-7R4 series engines meet the Smoke and Gaseous Emission requirements of 40 CFR Part 87, dated December 30, 1982. NOTE 15. All JT9D-7R4 series engines meet the January 1, 1975, fuel venting emission requirements of SFAR-27. NOTE 16. For JT9D-7R4D engines, EEC software versions -007 or -010, there exists, within the EEC, logic which will result in the Maximum Continuous thrust rating being limited during enroute climb. This condition will occur only when setting Maximum Continuous thrust directly from takeoff thrust with the EEC on, the thrust level positioned full forward, and following a climb of more than 3,000 feet above the runway. The difference between the limit and the Maximum Continuous thrust when taking off from a sea level airport is as follows: For engines incorporating the 154CF3 P2T2 probe (P/N 786464) and resistor harness (P/N 795644) the Difference varies from 0 at 3,000 feet to a maximum of 0.15 EPR at 14,000 feet. For engine incorporating the 154CF7 P2T2 (P/N 798133) the difference varies from 0 at 3,000 feet to a Maximum of 0.06 EPR at 14,000 feet. Thrust will not be limited if taking off from an airport of 4,300 feet or higher. For either engine configuration, Maximum Continuous thrust will not be limited when either an altitude of 14,000 feet or a Mn of .47 has been attained or if maximum climb thrust has been set. Maximum Continuous thrust is not limited with the EEC turned off. NOTE 17. Electronic Engine Control JT9D-7R4E1 (AI500) JT9D-7R4E1 (AI600) Ham. Std. Ham. Std. 769370-3 787240-1 NOTE 18. For JT9D-7R4E4 engines fitted with P&W P/N 792842 and 794731 fuel nozzles, the nozzles must be replaced with new or shop cleaned nozzles, or on-wing cleaned per the approved maintenance manual procedures at intervals not to exceed 700 flight cycles. NOTE 19. The following JT9D engine models and their associated data have been removed from this Type Certificate Data Sheet as of revision 11, since they are not currently installed on certificated aircraft: JT9D-70 JT9D-59D JT9D-70D JT9D-70B JT9D-7Q1 JT9D-7R4A JT9D-7Q2 JT9D-7R4H2 JT9D-59B NOTE 20. Use of takeoff thrust for more than five minutes (not to exceed ten minutes) is approved for use only in the event of an inoperative engine due to shutdown or failure. ----END----