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 |  | B  | All axial or radial  | Axial or radial cracks  |
 |  |  | cracks or hole to hole | on the leading edge,  |
 |  |  | cracks at the tip or  | airfoil or tip area are  |
 |  |  | leading edge are  | permitted.  |
 |  |  | permitted.  | Holes that are broken  |
 |  |  | No connected cracks or | through to the internal  |
 |  |  | areas where material  | cavity that are in the  |
 |  |  | will break off.  | limits are permitted.  |
 |  |  |  |  |
 |  |  |  |  |
 |  |  | NOTE:____  REMOVE ENGINE  | NOTE:____ REMOVE ENGINE  |
 |  |  | IMMEDIATELY IF THERE  | IMMEDIATELY IF THERE IS  |
 |  |  | IS IMMINENT PART  | IMMINENT PART FAILURE OR |
 |  |  | FAILURE OR IMMINENT  | IMMINENT MATERIAL  |
 |  |  | MATERIAL LIBERATION.  | LIBERATION.  |
 |  |  |  |  |
 |  |  |  | REMOVE ENGINE WITHIN 5  |
 |  |  |  | CYCLES IF ANY REDUCED  |
 |  |  |  | INTERVAL INSPECTION  |
 |  |  |  | LIMITS ARE E CEEDED.  |

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
~..............................................................................
 | TABLE 610 |
 ................................................................................

 |  |  |  1ST-STAGE HPT BLADE  |
 |  |  |  CONTINUE-IN-SERVICE LIMITS  |
 |  CONDITION  |  .....................................................
 |  FOUND  |  BLADE  | PERMITTED WITH REGULAR | PERMITTED WITH DECREASED |
 |  FIGURE 622  |  AREA  |  TIME INSPECTION  |  TIME INSPECTION  |

 ................................................................................ | Axial or Radial| C | All quantities of | All quantities of | | Cracks | | platform edge cracks | platform edge cracks | | | | that do not go into the| that go into the | | NOTE:_____See the | | platform to airfoil | platform to airfoil | | subsequent | | fillet radius and | fillet radius UP TO | | limits for open| | do not have signs of | 0.250 INCH (6.350 mm) | | cracks. | | platform curling. | RADICALLY PAST THE | | Material tears | | | RADIUS INTO THE AIRFOIL. | | are the same | | | | | as cracks. | ____ | NOTE: |
| NOTE: REMOVE ENGINE ____REMOVE ENGINE | | | WITHIN 5 CYCLES IF | WITHIN 5 CYCLES IF ANY | | | | THERE ARE ANY CRACKS | REDUCED INTERVAL | | | | IN THE RADIUS THAT GO | INSPECTION LIMITS ARE | | | | IN A CHORDWISE | EXCEEDED. | | | | DIRECTION. | | | | | | | ................................................................................ | Holes that are | A | None is permitted. IMMEDIATELY REMOVE THE ENGINE.| | Broken or ............................................................... | Burned through | B | None | On each blade, one piece | | to the Internal| | | that is missing from the | | Cavity | | | tip or one hole that is | | | | | less than 0.125 square | | | | | inch (81.0 square mm) in | | | | | area. No more than five | | | | | blades with these holes | | | | | on each rotor. | | | | | | | | | NOTE: If the hole is more|
| ____ | | | | than the decreased time | | | | | limits, but fully in area| | | | | B, remove the engine in | | | | | 50 cycles. If the hole | | | | | goes out of area B, | | | | | remove the engine in five| | | | | cycles or immediately. | ....................................................…........................... | Bent | B | A bent tip is permitted if the damage is not more | | Tip | | than other damage limits. | ................................................................................
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