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 NOTE: Cracked retainers will let the aft end of the
____ HPT shroud fall. This will wear the trailing edge of the HPT blades, and will cause the EGT to increase quickly. Continued operation with this condition will cause the HPT shroud to be removed from the HPT shroud support/LPT nozzle assembly.
 2)  A maximum service extension of 25 cycles is permitted if the HPT blade tip trailing edge is not into the tip cap and no HPT shrouds are extended into the gas path.
 S 216-099-C00
 (8)  Do the inspection of the 1st-Stage LPT NGV's again with the S18 borescope port.
 (a)  Use the limits previously given.
 S 216-096-C00
 (9)  Do the inspection of the HPT shrouds again with the S18 borescope port.
 (a)  Use the limits previously given.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
HPT Blades and Shrouds and 1st-Stage LPT NGV's - Inspection
___________________________________________________________
 S 216-110-C00
 (10) Prepare to examine the HPT blades.
 (a)  
Adjust the rigid borescope in the port to see the HPT blades.

 (b)  
Turn the N2 rotor to examine the 72 HPT blades and stop at each blade for a detailed inspection.

 (c)  
If this procedure shows that the HPT blade have damage caused by FOD, you must do this procedure: Combustion Chamber and HPT NGV Inspection.

 S 216-098-C00
 (11) Examine the HPT blades (Except the leading edges)
 (Fig. 607 and Fig. 607A).

 NOTE: The leading edges of the HPT blades are examined with the
____ flexible borescope. The flexible borescope is also used to examine the parts of the HPT blades which cannot be seen with the rigid borescope.
 (a)  Examine all the HPT airfoil surfaces for missing coating.
 1)  There is no maximum limit to the quantity of the CODEP coating material that is missing.
 NOTE: To help make an estimate of the size of damage
____ you see, the radial spacing of the trailing edge slots is approximately 0.1 inch (2.5 mm).
 (b)  Examine the trailing edges of the blades. 1) Blades that have cracks in area C are not serviceable. 2) Blades that have cracks in area B
 a) These cracks are not serviceable. b) A maximum service extension of 10 cycles is permitted if the trailing edge cracks in area B are less than
 0.05 inch (1.3 mm) in length.
 3)  Blades that have cracks in area A a) One crack is permitted if it is less than 0.1 inch
 (2.5 mm) in length.
 b)  A maximum service extension of 10 cycles is permitted if the trailing edge cracks are less than 0.20 inch (5 mm) in length.
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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 ////////////////////////

RADIAL CASTING CORE LINES 
A 
____NOTE:  DIMENSIONS ARE IN INCHES WITH MILLIMETERS IN PARENTHESES.  1200397-00-A 

Example HPT Rotor Blade Damage
Figure 607A (Sheet 1)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
B43041
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
NO. 3 RADIAL

GMM-1110724-00-A
Example HPT Rotor Blade Damage Figure 607A (Sheet 2)
B43094
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