|  |  |  3RD-STAGE LPT BLADE CONTINUE-IN-SERVICE LIMITS  |
 |  CONDITION  |  ................................................... ..
 |  FOUND  |  BLADE  |  SERVICEABLE  |  REMOVE THE ENGINE  |
 |  (FIGURE 626)  |  AREA  |  LIMITS  |  BEFORE THE 6TH CYCLE  |

 ................................................................................ | Deterioration | A,B,C,D | All deterioration in | All deterioration in the | | of the Surface | and E | the surface layer is | surface layer is | | Layer | | permitted. | permitted. | ................................................................................ | Burned Areas | A,C,D | No burned areas or | All burned areas or | | or Erosion | | erosion is permitted. | erosion that is no more | | | | | than 0.020 inch | | | | | (0.508 mm) in depth and | | | | | 0.300 inch (7.620 mm) | | | | | in diameter. | | ............................................................... | | B | No burned areas or | All burned areas or | | | | erosion is permitted. | erosion that is no more | | | | | than 0.010 inch | | | | | (0.254 mm) in depth and | | | | | 0.300 inch (7.620 mm) | | | | | in diameter. | | ............................................................... | | E | All burned areas or | All damage that is more | | | | erosion that is no more| than the SERVICEABLE | | | | than 0.020 inch | LIMITS | | | | (0.508 mm) in depth and| | | | | 0.300 inch (7.620 mm) | | | | | in diameter. | | ................................................................................ | Sulfidation | A,B,C,D | No sulfidation is | On each blade, one area | | | and E | permitted. | that is no more than | | | | | 0.200 square inch | | | | | (5.080 square mm) in area| | | | | and no material that is | | | | | missing. On each rotor, | | | | | no more than five blades | | | | | with sulfidation. | ................................................................................ | Blade Extension| A | No blade extension is | No blade extension is | | | | permitted. | permitted. | | | .........................…........................... | | ____
| NOTE: A sign of blade extension is an increase in | | | | the length and a decrease in the perimeter. | 2................….........…...................................................1
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
No. 19 - LPT Blades (3rd-Stage) Inspection
__________________________________________
 (a)  If the damage is not more than the limits, then the airplane can continue to operate.
 S 416-205-N00
 (6)  
Install the access port AP-10 (Fig. 623):

 (a)  
If the access port AP-10 is disassembled, assemble it for the installation.

 NOTE: The plug assembly is not usually disassembled.
____
 1)  When you install the spring tension washer in the cover recess, make sure these conditions occur: the outer diameter of the washer touches the cover, and the concave surface of the washer is adjacent to the cover.
 2) From the washer side, put the plug in the assembled washer and cover. 3) Push the cotter pin in the plug until the cotter pin head is tightly against the flat side of the plug.
 (b)  With the split side to the inner side, install the plug with a new AP-10 gasket (PWA ST1146-08).
 NOTE: The plug will be in the case boss and the spring washer
____ will push the plug to the inner side.
 (c)  
Attach the plug stop cover to the plug (AP-10).

 (d)  
Fully clean the bolt threads and the plug threads with petroleum solvent.

 NOTE: This removes unwanted carbon and all used antigalling
____
 compound.

 (e)  
Apply a layer of Silver Goop to the threads of the bolts and remove the unwanted compound.

 (f)  
Attach the plug stop to the access port boss with the bolts.

 (g)  
Tighten the bolts to 54-60 pound-inches (6.1-6.8
 newton-meters).

 (h)  
Install lockwire on the AP-10 plug.

 (7)  
Do this task: Put the Airplane Back to its Usual Condition.

 S 416-206-N00
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