747-400 AMM 飞机维护手册 发动机 ENGINE 1(82)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
~............................................................................... | TABLE 609 | ................................................................................. | | | 1ST-STAGE HPT VANES | | | | CONTINUE-IN-SERVICE LIMITS | | CONDITION | ........................................................ | FOUND | VANE | PERMITTED WITH REGULAR | PERMITTED WITH DECREASED | |FIGURE 621 | AREA | TIME INSPECTION | TIME INSPECTION | ....................................................…............................
 |  |  | ON EACH VANE:  | ON EACH VANE:  |
 |  |  | No more than three cracks| No more than three cracks |
 |  |  | that connect three adja- | that connect five adjecent|
 |  |  | cent cooling air holes or| cooling air holes or go to|
 |  |  | go to a concave or convex| a concave or convex air- |
 |  |  | airfoil cooling air hole.| foil cooling air hole. No |
 |  |  | No circular cracks or  | circular cracks or areas  |
 |  |  | areas where material will| where material will break |
 |  |  | break off are permitted. | off are permitted.  |
 |  |  ........................................................
 |  |  | One crack that goes from | Two cracks that go from  |
 |  |  | the inner diameter or the| the inner diameter or the |
 |  |  | outer diameter platform  | outer diameter platform to|
 |  |  | to a maximum height or  | a maximum height or dis- |
 |  |  | distance of not more than| tance of not more than  |
 |  |  | 0.5 inch (12.7 mm) from  | 0.750 inch (19.050 mm)  |
 |  |  | the platform.  | from the platform.  |

 | ........................................…............................ | | Concave | All quantities of cracks that are less than 0.15 inch| | | Airfoil | (3.810 mm) in length | | | Surface | | | | (View B) | Adjacent surfaces that are at levels that are not | | | | more than 0.0312 inch (0.792 mm) apart. | | | | | | | | No circular cracks or areas where material will break| | | | off. | | | | | | | ____All parts of cracks that are burned or have
| NOTE: | | | | erosion with an opening more than 0.05 inch | | | | (1.27 mm) in width are the same as holes; the | | | | burned and broken hole limits are applicable. | | | | | 2...........…............…......................................................1
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
 72-00-00
 ALL  ú ú N02 Page 684H ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
~............................................................................... | TABLE 609 | ................................................................................. | | | 1ST-STAGE HPT VANES | | | | CONTINUE-IN-SERVICE LIMITS | | CONDITION | ........................................................ | FOUND | VANE | PERMITTED WITH REGULAR | PERMITTED WITH DECREASED | |FIGURE 621 | AREA | TIME INSPECTION | TIME INSPECTION | ....................................................…............................ | Cracks, | Concave | Three axial cracks that | All quantities of axial | | Axial and | Airfoil | go from one cooling hole | cracks that go from one | | Radial | Surface | group to 66% of the dis- | cooling hole group to the | | | (View B) | tance to the adjacent | adjacent group, or from | | | | cooling hole group, or | the trailing edge to the | | | | from the trailing edge to| rear cooling hole group, | | | | 66% of the distance to | if the cracks do not make | | | | the rear cooling hole | circular cracks, and | | | | group. | material will not break | | | | | off. | | | | One of the three permit- | | | | | ted axial cracks can go | | | | | from one cooling hole | | | | | group to the adjacent | | | | | cooling hole group, or | | | | | from the trailing edge | | | | | through the rear cooling | | | | | hole group to the adja-| | | | | cent cooling hole group. | | | | ...........................…............................ | | | Radial cracks that go on the concave airfoil surface | | | | from the inner diameter or outer diameter platform | | | | (buttress) are permitted. | | | ........................................................ | | | Radial cracks on a | Radial cracks on a | | | | platform surface can go | platform surface can go a | | | | a maximum of 0.5 inch | maximum of 0.8 inch | | | | (12.7 mm) on the airfoil | (20.32 mm) on the airfoil | | | | surface. | surface. | | | ...........................…............................ | | | Cracks on inner diameter or outer diameter platforms | | | | cannot connect with cracks on the airfoil surface. | 2...........…............…......................................................1
　
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