GEARBOX - MAIN 72-61-01 Inspection/Check 601 ALL Cleaning/Painting 701 ALL
 GEARSHAFT AND BEARINGS ASSEMBLY 72-61-14
 -EEC ALTERNATOR DRIVE Removal/Installation 401 ALL HOUSING - FILTER, MAIN OIL 72-61-11 Removal/Installation 401 ALL SEAL - OIL, DEOILER DRIVE 72-61-02 Removal/Installation 401 ALL SEAL - OIL, EEC ALTERNATOR DRIVE 72-61-05 Removal/Installation 401 ALL
 SEAL - OIL, FUEL PUMP DRIVE  72-61-06 Removal/Installation 401 ALL
 72-CONTENTS
 NGUN Page 7 Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
CHAPTER 72 - ENGINE
 TABLE OF CONTENTS
_________________
 Chapter Section Subject_______ Subject ____ Effectivity
_______ Page ___________
 SEAL - OIL, HYDRAULIC PUMP DRIVE 72-61-07
 Removal/Installation 401 ALL
 SEAL - OIL, INTEGRATED DRIVE 72-61-04
 GENERATOR (IDG) DRIVE
 Removal/Installation 401 ALL
 SEAL - OIL, STARTER DRIVE 72-61-03
 Removal/Installation 401 ALL
 GEARBOX 72-62-00

 GEARBOX - ANGLE 72-62-01 Removal/Installation 401 ALL Inspection/Check 601 ALL
 72-CONTENTS
 NGUN Page 8 Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
ENGINE - DESCRIPTION AND OPERATION
__________________________________
 1.  General
_______
 A.  The engine is a two-spool, axial flow turbofan engine of high compression and bypass ratio, having 16 compressor stages, an annular combustion chamber, and 6 turbine stages. The low pressure system consists of a five stage low pressure compressor (LPC) and a four stage low pressure turbine (LPT), mechanically independent of the high pressure system which consists of an eleven stage high pressure compressor (HPC) and a two stage high pressure turbine (HPT). The engine cases, when bolted together, form a structurally rigid support for the engine, with internal parts supported through struts and bearings. The engine mounts are located at the 12 o'clock position on the intermediate case and turbine exhaust case.
 B.  The engine is made up of four main sections: Compressor Section (AMM 72-30-00/001), Combustion Section (AMM 72-40-00/001), Turbine Section (AMM 72-50-00/001), and Accessory Drives (AMM 72-60-00/001).
 C.  The engine without QEC equipment installed is 132.7 inches (337.1 cm) long and approximately 97 inches (246 cm) across the largest diameter. The bare engine weight is approximately 9200 pounds (4173 kg). Basic engine specifications are provided in Fig. 1.
 2.  Engine Modules (Fig. 2)
______________
 A.  Figure 2 illustrates the engine build groups and major sections of the engine.
 3.  Engine External Components (Fig. 3)
__________________________
 A.  Figure 3 illustrates the location of major engine components and component nomenclature. ATA references to component removal/installation procedures are also provided.
 4.  Engine Flange Identification (Fig. 4)
____________________________
 A.  Engine flanges are identified in alphabetical sequence from the front to the rear of the engine.
 5.  Designation of Engine Stations (Fig. 5)
______________________________
 A.  Certain specific points along the engine axial profile are identified by station number to provide ease of reference to items such as component locations, test taps, and sensor locations.
 6.  Compressor Section
__________________
 A.  The compressor section consists of the low pressure compressor (LPC), low pressure compressor (LPC)/low pressure turbine (LPT) coupling, fan case, intermediate case, and high pressure compressor (HPC).
 B.  Low Pressure Compressor (LPC) (Fig. 6)
 (1)  The LPC consists of a five stage (1st-, 1.6-, 2nd-, 3rd-, and 4th-stage) rotor and a four stage (1st-, 1.6-, 2nd-, and 3rd-stage) stator. The LPC stator and rotor assembly provides the initial compression of the ambient (inlet) air which is then ducted through the intermediate case to the HPC. The compressor inlet cone mounted on the front compressor hub provides a smooth aerodynamic fairing at the inlet of the LPC.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
 72-00-00
 ALL  ú ú N01 Page 1 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
　
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