(7)  
The HPT rotor, 72-52-00, is a single-stage, air-cooled turbine. Structurally, the rotor consists of the front shaft, the forward air seal, the disk, and the rear shaft. The HPT rotor drives the HPC rotor and is directly connected to it by a bolted flange to form what is essentially a single core rotor. The rotor is internally cooled by low pressure compressor (booster) discharge air. It has interference rabbetted flanges for rigidity and stability.

 (8)  
The HPT shroud and 1st-stage LPT nozzle, 72-53-00, is located in the aft section of the combustion case. It forms the interface between the core section and the LPT module of the engine. The forward flange of the assembly is rabbetted and bolted to the inner surfaces of the combustion casing. The aft flange is bolted between the combustion casing aft flange and the LPT stator forward flange.

 4.  Low Pressure Turbine (LPT) Major Module (Fig. 3)
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 A.  The low pressure turbine module consists of 3 maintenance modules as follows: low pressure turbine, low pressure turbine shaft, and turbine frame.
 (1)  
The low pressure turbine, 72-54-00, consists of the LPT case (which contains the LPT stator) mounted between the combustion casing and the turbine frame and the 4-stage, axial type LPT rotor, supported by the LPT shaft.

 (2)  
The LPT shaft module, 72-55-00, connects the fan shaft to the LPT rotor. It consists of the LPT shaft, LPT stub shaft, center vent tube and center vent tube rear extension duct. The LPT shaft aft end is supported by the No. 5 bearing located in the turbine frame, and the shaft forward end is coupled to the fan shaft. The LPT shaft has 2 functions: coupling the fan and booster rotors with the LPT rotor, and providing for HPC rear support through the No. 4 bearing. In addition, the LPT shaft houses the center vent tube of the forward and aft engine oil sumps.

 (3)  
The turbine frame, 72-56-00, is the major structural assembly at the rear of the engine. It supports the LPT rotor rear section and provides mounts for attaching the rear of the engine to the airplane strut and for ground handling. The frame, a fabricated structural weldment, consists of a central hub and a polygonal outer casing, connected through slanted struts. The struts support a midstream fairing on the forward side and the exhaust plug on the aft side.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
5.  Accessory Drive System (Fig. 3 and 4)
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 A.  The accessory drive system consists of 2 maintenance modules, the transfer gearbox and the accessory gearbox.
 (1)  
The transfer gearbox (TGB), 72-62-00, provides power transmission between the inlet gearbox (IGB) and the accessory gearbox (AGB) and includes the following major parts: radial drive shaft, TGB, and horizontal drive shaft. The radial drive shaft assembly is installed inside fan frame strut No. 10 and consists of the radial drive shaft and the shaft mid-length bearing. The TGB is mounted on the fan frame at the 9 o'clock position and consists of a housing and a set of 2 bevel gears. The horizontal drive shaft assembly provides power transmission between the TGB and AGB and consists of a housing, a bevel gear and a horizontal drive shaft.

 (2)  
The accessory gearbox, 72-63-00, is mounted on the fan case, between 6 and 9 o'clock position. It houses a gear train that reduces and increases the rotational speed to meet the specific drive requirements of each accessory. Most of the accessories are installed on the gearbox pads through quick attach/detach (QAD) provisions.

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 72-00-00
 ALL  ú ú C01 Page 10 ú Feb 25/85
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ENGINE - TROUBLE SHOOTING
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 1. Trouble Shoot the Engine
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