737-300 400 500 AMM 飞机维护手册 ENGINE 发动机 1(46)

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 (c)  Distorted leading edges because of overtemperature. 1) Distortion of the leading edges is not serviceable.
 a)  If not serviceable, a maximum service extension of 15 cycles or 25 hours is permitted if the distortion is less than 0.8 inch (20 mm) on the 1st Stage LPT blades blades and 0.08 inch (2 mm) on all other blades.
 NOTE: Overtemperature damage can be seen on a
____ blade as melted areas or a blade with parallel grooves in the blade hard coat.
 2)  If you see a gold coloration of the 1st Stage blades, do an inspection of the fuel filter cartridge (AMM 73-11-02/601).
 (d)  Tip Shroud Interlock Gaps (Fig. 608).
 1)  Tip Shroud Interlock gaps are servicable for the 1st Stage if the interlock faces do not show wear. a) If not serviceable, a maximum service extension of 5
 cycles is permitted.
 2)  Tip Shroud Interlock gaps are not serviceable for Stages 2 and 3. a) If not serviceable, a maximum service extension of 5
 cycles is permitted.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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 ////////////////////////
Low Pressure Turbine (LPT) Rotor Blade (1st thru 3rd Stage) - Inspection
________________________________________________________________________
 (e)  
Shingled or Unlatched Tip Shrouds (Fig. 608). 1) Shingled or Unlatched Tip Shrouds are not serviceable.

 a)  If not serviceable but rotor turns freely and engine vibration is not excessive, a maximum service extension of 5 cycles or 10 hours is permitted in a shingled or unlatched condition.

 (f)  
Cirumferential looseness is serviceable.

 (g)  
Seal Teeth wear is serviceable under these conditions. 1) Wear must be less than 1/2 of tooth height if only one stage is affected. 2) Wear must be less than 1/3 of tooth height if 2 stages are affected.

 3)  Wear must be less than 1/4 of tooth height if 3 stages are affected.

 (h)  
Flaking on the hardened seal teeth is serviceable.

 S 416-094-C00
 CAUTION: MAKE SURE YOU INSTALL THE CORRECT BORESCOPE PLUG IN THE CORRECT
_______ LOCATION. THE BORESCOPE PLUG TO THE LPT STAGE 1 AND COMBUSTION CASE HAVE THE SAME THREAD SIZE. THE STEM OF THE BORESCOPE PLUG TO THE LPT STAGE 1 NOZZLE WILL BE BURNED AWAY IF IT IS INSTALLED IN THE BORESCOPE PORT TO THE COMBUSTION CASE.
 (6)
Do these steps to install the borescope plugs (Fig. 606A):

 (a)  
Apply a light layer of graphite grease (CP2101) on the borescope plug threads and the mating surfaces.

 (b)  
Install in the borescope ports.

 (c)  
Tighten the plugs to 57-63 pound-inches (6.4-7.1 Newton meters).

 (d)  
Put a lockwire on the plug.

 

 (7)
Do the procedure to put the airplane back to its usual condition.

 S 846-053-C00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
A
SEE A
S20 SEE C
B B
G-M56-NT-0035(1)-00-B 
S21  A 
SEE  D  S17  TOP VERTICAL 
S22  SEE  B 
SEE E 
A 
STAGE  BLADES NO. OF  VIEW PORT NO. LEADING EDGE  VIEW PORT NO. TRAILING EDGE 
1  174  S17 - S18  S20 
2  162  S20  S21  S18 
3  157  S21  S22  S17 
4  160  S22  -
1ST-STAGE LPT BORESCOPE PORT LOCATION 
(AFT LOOKING FORWARD) 
A-A 
Low Pressure Turbine Inspection 
Figure 608 (Sheet 1) 

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