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 B.  The 1st-stage disk has 174 tip-shrouded, nickel alloy blades with anti-wear shields. The front of the blade roots has a retaining lug which houses a retaining ring. The retaining ring provides axial retention for blades and is held axially by the blade retainer.
 C.  The 2nd- thru 4th-stages of the the LPT rotor are similar except for the following differences. The 2nd-stage LPT disk has 162 blades with anti-wear shields, the 3rd-stage LPT disk has 157 blades, and the 4th-stage LPT disk has 160 blades with anti-shingling shims. Nickel alloy rotating air seals provide the axial stop for the retaining rings. A conical rotor support is sandwich-mounted between the 3rd-stage rotating air seal and the 3rd-stage disk.
 D.  The conical rotor support, made of nickel alloy, provides a connection between the disks and the LPT stub shaft. It divides the LPT rotor inner enclosure into two separate cavities.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 72-54-00
 ALL  ú ú C01 Page 4 ú Oct 25/85
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
LOW PRESSURE TURBINE - INSPECTION/CHECK
_______________________________________
 1.  General
_______
 A.  This procedure contains the data for two inspections as follows:
 (1)  
The Low Pressure Turbine (LPT) Inspection

 (2)  
The General Low Pressure Turbine (LPT) Inspection

 B.  To get access the LPT area you must open the thrust reverser and fan cowl panels.
 C.  To examine the pre-twist of the 4th-stage LPT blades, refer to
 AMM 72-00-00/601.

 D.  For this procedure the Low Pressure Turbine will be referred to as the LPT.
 TASK 72-54-00-216-001-C00
 2.  Low Pressure Turbine (LPT) Inspection
_____________________________________
 A.  General
 (1)  This task contains two procedures for the LPT case inspection as follows:
 (a)  
The LPT Casing Inspection

 (b)  
The Cooling Air Tube Inspection

 B.  References
 (1)  
AMM 71-11-02/201, Fan Cowl Panels

 (2)  
AMM 78-31-00/201, Thrust Reverser System

 C.  Access
 (1)  
Location Zones
 502/602 Left Fan Cowl Panels
 503/603 Right Fan Cowl Panels
 504/604 Left Thrust Reversers
 505/605 Right Thrust Reversers
 506 Engine No. 1
 606 Engine No. 2

 (2)  
Access Panels
 5737L Engine No. 1 - Right Fan Cowl Panel
 5738L Engine No. 1 - Left Thrust Reverser
 5739L Engine No. 1 - Right Thrust Reverser
 5746L Engine No. 1 - Left Fan Cowl Panel
 5837R Engine No. 2 - Right Fan Cowl Panel
 5838R Engine No. 2 - Left Thrust Reverser
 5839R Engine No. 2 - Right Thrust Reverser
 5846R Engine No. 2 - Left Fan Cowl Panel

 

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 72-54-00
 ALL  ú ú C01 Page 601 ú Nov 15/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
D. Procedure
 S 016-002-C00
 (1)  Open the left and right fan cowl panels (AMM 71-11-02/201).
 S 016-004-C00
 WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN THE
_______ THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURY TO PERSONS OR DAMAGE TO THE EQUIPMENT CAN OCCUR.
 (2)  Open the left and right thrust reversers (AMM 78-31-00/201).
 E. LPT Casing Inspection
 S 216-005-C00
 (1)  Examine the casing for cracks (Fig. 601):
 (a)  
All cracks are permitted if they are not more than 0.04 inch

 (1.00 mm) in length and with a minimum distance of 2.0 inches
 (51.0 mm) between all other cracks.

 (b)  
A maximum service extension of 10 cycles is permitted for one crack 0.4 inch (10.2 mm) in length.
　
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