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 1.  General
_______
 A.  The turbine frame is the major structural assembly at the rear of the engine (Fig. 1). It supports the low pressure turbine (LPT) rotor rear section and provides for engine rear mounting on the airframe.
 B.  The turbine frame consists of the following major conponents:
 (1)
Turbine frame

 (2)
No. 5 bearing support

 2.  Turbine Frame
_____________
 A.  The turbine frame assembly is a nickel alloy weldment consisting of a central hub and a polygonal outer casing, connected through slanted struts. The struts support a fairing on the forward side and the exhaust plug on the aft side.
 B.  Twelve struts are arranged in a slanted position relative to the hub to provide the turbine frame with correct bending stiffness. These struts are hollow and provide passage for the following:
 (1)
Aft sump oil scavenge tube (No. 5 strut)

 (2)
No. 4 and 5 bearings oil supply tube (No. 6 strut)

 (3)
Aft sump overboard seal drain tube (No. 7 strut)

 C.  The front flange of the outer casing is bolted to the LPT case. Its rear flange supports the primary exhaust nozzle. At its periphery there are eight clevis mounts for engine/airplane systems adaptation and handling.
 D.  The hub inner front flange carries the No. 5 bearing support. The inner rear flange has a flange assembly supporting the flame arrestor and oil inlet cover.
 3.  No. 5 Bearing Support
_____________________
 A.  The No. 5 bearing support is made of steel alloy. Its outer flange is bolted to the turbine frame and supports the aft oil sump. Its inner flange houses an adjusting sleeve and the No. 5 bearing outer race. The rear face of the support carries the oil inlet cover which supports the oil supply manifold for the No. 4 and No. 5 bearings and provides for pressurizaton of the rotary air/oil separator installed at the rear end of the center vent tube rear extension duct. The oil inlet cover also centers the rear extension duct. The No. 5 bearing support has machined passages for:
 (1)
Pressurizing air to the oil inlet cover

 (2)
Sump bleed air to the center vent tube

 (3)
Oil to the scavenge tube

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 72-56-00
 ALL  ú ú C01 Page 1 ú Oct 25/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////

Turbine Frame Location
Figure 1

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 72-56-00
 ALL  ú ú C01 Page 2 ú Mar 15/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////

N0. 5 STRUT  NO. 6 STRUT  FWD  NO. 7 STRUT 
S-M56-MM-0309-(1)-00-B 
Turbine Frame Struts Location 
Figure 2 

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 72-56-00
 ALL  ú ú C01 Page 3 ú Oct 25/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
TURBINE FRAME - INSPECTION/CHECK
________________________________
 1.  General
_______
 A.  This procedure contains three tasks. The tasks are as follows:
 -General Turbine Frame Inspection
 -
Turbine Frame Exhaust Struts and Attach Points and Mounting Lug Inspection

 -
Turbine Frame Oil Supply and Scavenge Tube Inspection

 B.  Examine only the external areas.
 C.  Access to the turbine frame is through the open fan cowl panel and thrust reverser.
 TASK 72-56-00-216-001-C00
 2.  General Turbine Frame Inspection
　
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