ENGINE JT8D BOEING 737-200
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ENGINE JT8D BOEING 737-200

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ENGINE JT8D COURSE, BOEING 737-200, a special thanks to NECTALI MESSALA YOVERA for the diapositives.

ENGINE JT8D COURSE, BOEING 737-200, a special thanks to NECTALI MESSALA YOVERA for the diapositives.

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  • Dear Ricardo;
    Kindly advise deference Between JT8D-17 andJT8D-17A
    Thank you&best Regards;
    Fouad Elawady
    AWA EGYPTIAN AVIATION
    Ph :00201007333311
    Email: fdawady@awa-aviation.com
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ENGINE JT8D BOEING 737-200 Presentation Transcript

  • 1. JT8D ENGINE GENERALIDADES DESCRIPCION Y OPERACIÓN FUNCIONAMIENTO DEL MOTOR LOCALIZACION Y DETALLESCOMPONENTES. PRACTICAS DE MANTENIMIENTO DESCARTE DE FALLAS
  • 2. DESIGNATION OF THE ENGINE JT8DJ = Motor de Reacción (JET)T = Turbo ventilador ( turbofan)8 = Modelo Básico de DuctoCompletoD = Motor que opera sinInyección de agua.-17 = N° de Modificaciones
  • 3. HISTORY OF THE JT8DEL JT8D ES UN MOTOR DE FLUJO AXIAL DE DOBLEFLUJO TOTALMENTE DUCTEADO. EL PROYECTO DELMOTOR TURBOFAN FUE INICIADO EN ABRIL DE 1960.- FEBRERO 1963 JT8D-1 CERTIFICADO A 14,000 LBS. DE EMPUJEENTRANDO EN SERVICIO EN 1964.- ABRIL 1963 JT8D-5 CERTIFICADO A 12,000 LBS DE EMPUJE.- MARZO 1966 JT8D-7 CERTIFICADO A 14,000 LBS DE EMPUJE.- MAYO 1967 JT8D-9 CERTIFICADO A 14,500 LBS DE EMPUJE.- SETIEMBRE 1968 JT8D-11 CERTIFICADO A 15,000 LBS DE EMPUJE.- ABRIL 1971 JT8D-15 CERTIFICADO A 15,500 LBS DE EMPUJE.- FEBRERO 1974 JT8D- 17 CERTIFICADO A 16,000 LBS DE EMPUJE.- ABRIL 1976 JT8D-17R CERTIFICADO A 16,400 LBS DE EMPUJE17,400 LBS DE EMPUJE.
  • 4. GENERAL ZONE DIAGRAM (MM 12-31-1)
  • 5. GENERAL ZONE DIAGRAM (MM 12-31-1)
  • 6. ENGINE SAFETY PRECAUTIONS
  • 7. ENGINE SAFETY PRECAUTIONS
  • 8. ENGINE SAFETY PRECAUTIONS
  • 9. LEFT ENGINE COWLING
  • 10. RIGHT ENGINE COWLING
  • 11. HUSH KIT MODIFICATION
  • 12. HUSH KIT MODIFICATION
  • 13. POWERPLANT ATTACHMENT POINT
  • 14. POWERPLANT – FORWARD ENGINE MOUNT
  • 15. POWERPLANT – AFTER ENGINE MOUNT
  • 16. POWERPLANT - LEFT SIDE VIEW
  • 17. POWERPLANT - RIGHT SIDE VIEW
  • 18. POWERPLANT - ENGINE GENERAL
  • 19. TECHNICAL SPECIFICATIONS
  • 20. GENERAL STATIONS
  • 21. MAJOR JT8D DESIGN FEATURES
  • 22. DIRECTIONAL REFERENCESVIEWED FROM REAR
  • 23. ENGINE FLANGES AND STATIONS
  • 24. BEARING LOCATIONS
  • 25. PRATT AND WHITNEY JT8D ENGINE
  • 26. ENGINE RIGHT SIDE
  • 27. ENGINE LEFT SIDE
  • 28. ENGINE BUILD GROUPS AND SECTION
  • 29. ENGINE FRONT VIEW AND ACCESSORY DRIVE CASE
  • 30. ENGINE FAN INLET GROUP
  • 31. ENGINE FAN INLET MASTER VANE
  • 32. FRONT COMPRESSOR GROUP
  • 33. COMPRESSOR INTERMEDIATE GROUP
  • 34. HIGH PRESSURE COMPRESSORROTORS QTYR7 60R8 58R9 60R10 64R11 70R12 80R13 74
  • 35. DIFFUSER GROUP
  • 36. FUEL INLET TUBES AND MANIFOLD
  • 37. REDUCED EMISSION TYPE FUEL NOZZLEAND SUPPORT
  • 38. COMBUSTION CHAMBERS
  • 39. DIFFUSER OUTER FAN DUCT GROUP
  • 40. FAN DISCHARGE SECTION
  • 41. REAR COMPRESSOR DRIVE TURBINE GROUP46 95 79 77
  • 42. LOW PRESSURE TURBINETURBINE SHAFTBEARING 4 1/2BLADES
  • 43. EXHAUST CASE GROUPTURBINE SHAFTBEARING 4 1/2
  • 44. PILOTS FWD OVERHEAD PANEL – P5
  • 45. FORWARD PANEL P-5
  • 46. FORWARD PANEL P-5
  • 47. FORWARD PANEL P-5APU CONTROLS AND INDICATION
  • 48. ENGINE CONTROLS PANEL P-2
  • 49. FLIGHT DECK ENGINE CONTROLS
  • 50. PANEL DETRÁS DEL ASIENTO DEL PRIMER OFICIAL – P6
  • 51. PANEL DETRÁS DEL ASIENTO DEL CAPITAN – P18
  • 52. INDICACION DE LUCES EN PANEL P5
  • 53. STATION HEIGHTA AIRCONDITIONING 528 3’ 4”B APU OIL TANK 1121 12”C EXT. POWER – AC 232 5’ 4”D ENGINE 1 OIL TANK 616 3’ 5”E ENGINE 2 OIL TANK 616 3’ 1”F HYDRAULIC RESERVOIR 664 4’ 5”G OVERWING FUELING 755 9’ 4”H OXYGEN 390 6’ 3”J PNEUMATIC CONNECTION 540 3’ 8”K POTABLE WATER 390 6’ 4”L PRESSURE FUELING 679 8’M TOILET PANEL , AFT. 996 7’N TOILET PANEL, FWD 270 5’ 10”O ACM OIL FILL 575 4’ 2”P EXT. POWER – DC 380 4’ 3”R CSD OIL FILL 625 3’ 3”S STARTER 630 3’ 3”T THRUST REVERSER ISOLATION 540 4’ 2”SERVICING POINTS
  • 54. ENGINE OIL SYSTEMATA - 79
  • 55. ENGINE CONTROLS PANEL P-2
  • 56. ENGINE CONTROLS PANEL P-2
  • 57. OIL SYSTEM LIMITS Normal Oil Pressure : 40 to 55 psi. Temperature :120º C, JT8D-1, -7, -9 ( Continuous)157º C, JT8D-1, -7, -9 ( Transient)130º C, JT8D-11, -15, -17 ( Continuous)165º C, JT8D-11, -15, -17 ( Transient) Breather:8.0 inch Hg, maximum, JT8D-1, -7, -98.5 inch Hg, maximum, JT8D-11, -15, -17 Consumption (per hour)½ pint to 1 quart normal (0.5 to 1 liter)2 quarts – recommend that cause be investigated
  • 58. ENGINE OIL SYSTEM EXTERNAL COMPONENTS
  • 59. ENGINE OIL SYSTEM COMPONENTS
  • 60. OIL TANKEXPANSION SPACE: 1.3 US gallosx“HOT” TANK
  • 61. TANK DRAIN VALVE
  • 62. ENGINE OIL QUANTITY TEST
  • 63. MAIN OIL PUMP
  • 64. MAIN OIL STRAINER INSTALLATIONDE PAPELc/20 Hrs.DE METALc/150-200 Hrs.CLEANABLEPRESS DROP: 5 PSICLEANABLEPRESS DROP: 7-9 PSIDISPOSABLEPRESS DROP: 3-4 PSI
  • 65. ENGINE OIL SYSTEM
  • 66. LOW OIL PRESSURE WARNING SYSTEM
  • 67. LOW OIL PRESSURE WARNING SYSTEM
  • 68. OIL FILTER BYPASS WARNING SYSTEM
  • 69. BEARING LOCATIONS
  • 70. TYPICAL CARBON AND LABYRINTH SEALS
  • 71. TYPICAL LABYRINTH SEALS
  • 72. TYPICAL CARBON SEALS
  • 73. TYPICAL ANTIFRICTION BEARINGS
  • 74. MAIN BEARING ROLLER BEARINGS – Support rotatingParts radially, they absorb angular loads ;They do not prevent axial movement. BALL BEARINGS – Hold rotating parts inaxial and radial alignment. They absorbboth thrust (axial) and angular loads
  • 75. ENGINE LUBRICATION SYSTEM
  • 76. LUBRICATION SYSTEM INDICATORS
  • 77. ENGINE OIL PRESSURE ADJUSTMENT ( MM 71-09-100 )
  • 78. GEARBOX ROTARY BRETHER IMPELLER
  • 79. ENGINEFUEL SYSTEMATA - 73
  • 80.  PROPORCIONA LA CANTIDAD DE COMBUSTIBLE ADECUADOPARA LA RELACIÓN DE COMBUSTIÓN COMPLETA PARA TODOSLOS REQUERIMIENTOS DE OPERACIÓN DEL MOTOR. LOS COMPONENTES SON:BOMBA DE COMBUSTIBLE.CALENTADOR DE COMBUSTIBLE.UNIDAD DE CONTROL DE COMBUSTIBLE.TRANSMISOR DE FLUJO.ENFRIADOR ACEITE-COMBUSTIBLE.VALVULA DE PRESURIZACIÓN Y DESCARGA.DISTRIBUIDORES E INYECTORES.FUEL SYSTEM
  • 81. FUEL SYSTEM COMPONENTS - LEFT SIDE
  • 82. FUEL SYSTEM COMPONENTS - RIGHT SIDE
  • 83. FUEL SYSTEM OVERVIEW
  • 84. ENGINE FUEL SYSTEM
  • 85. ENGINE FUEL SYSTEM DIAGRAM
  • 86. FUEL SYSTEM
  • 87. FUEL CONTROL UNITÑ
  • 88. JT8D - SIMPLIFIED FUEL CONTROL
  • 89. JT8D – FUEL PUMP
  • 90. FUEL HEAT SYSTEM
  • 91. ENGINE FUEL OVERHEAD PANEL P5-2
  • 92. ENGINE FUEL DEICING SYSTEM SCHEMATIC
  • 93. PRESSURIZING AND DUMP VALVE
  • 94. PRESSURIZING AND DUMP VALVE
  • 95. TYPICAL FUEL NOZZLES AND SUPPORTS
  • 96. FUEL NOZZLES AND SUPPORTS
  • 97. ENGINE INDICATINGATA - 77
  • 98. ENGINE PRESSURE RATIO CIRCUIT (EPR)
  • 99. ENGINE PRESSURE RATIO CIRCUIT (EPR)
  • 100. ENGINE PRESSURE RATIO CIRCUIT (EPR)
  • 101. ENGINE RPM INDICATING SYSTEMS
  • 102. EXHAUST GAS TEMPERATURE CIRCUIT
  • 103. EXHAUST GAS TEMPERATURE INDICATOR
  • 104. FUEL FLOW INDICATING SYSTEM
  • 105. VIBRATION INDICATING SYSTEM40 CPS
  • 106. ENGINE CONTROLSATA - 76
  • 107. ENGINE CONTROL SYSTEM
  • 108. FLIGHT DECK ENGINE CONTROLS
  • 109. ENGINE MOUNTED CONTROLS
  • 110. STARTINGATA - 80
  • 111. ENGINE STARTING SYSTEM
  • 112. ENGINE STARTING SYSTEM
  • 113. ENGINE START VALVE / STARTER
  • 114. PNEUMATIC START
  • 115. PNEUMATIC START
  • 116. PNEUMATIC STARTER
  • 117. ENGINE START CIRCUIT
  • 118. ENGINE START CIRCUIT
  • 119. IGNITIONATA - 74
  • 120. IGNITION SYSTEM COMPONENTS
  • 121. IGNITION SYSTEM COMPONENTS
  • 122. POWER PLANTAIRATA - 75
  • 123. ABBREVIATIONS P = Pressure psi, Kg/cm2 Ps = Static Pressure Pd = Dynamic Pressure Pt = Total Pressure = ( Ps+Pd ) Pam = Ambient Pressure Po. = International Standard Day pressure at sealevel 29,92” HgA, 14.7 psia, 760mm HgA,1013.2 Millibars HgA. To. = International Standard Day Temperature atsea level 59 degrees F, 15 degrees C. EPR = Engine Pressure Ratio= Turbine Discharge Total PressureCompresssor Inlet Total Pressure
  • 124. TYPICAL ANTI-ICING CONTROL AND INDICATION
  • 125. ENGINE AND NOSE COWL ANTI-ICING
  • 126. ANTISURGE BLEED SYSTEM CONFIGURATIONS
  • 127. START BLEED / ANTISURGE SYSTEM
  • 128. ANTISURGE BLEED SYSTEM
  • 129. PRESSURE RATIO BLEED CONTROL
  • 130. BLEED SYSTEM SCHEMATIC - CLOSED
  • 131. BLEED SYSTEM SCHEMATIC - OPEN
  • 132. BLEED CONTROL START VALVE
  • 133. ANTISURGE BLEED SYSTEM COMPONENTS
  • 134. EXHAUSTATA - 78
  • 135. THRUST REVERSER CONTROL SYSTEM
  • 136. THRUST REVERSER ELECTRICAL / HYDRAULIC SCHEMATIC
  • 137. REVERSER UNLOCKED LIGHT
  • 138. REVERSER UNLOCKED LIGHT OFF
  • 139. THRUST REVERSER ISOLATION VALVE / PRESSURE SWITCH
  • 140. QUIZ