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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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 | ....................................................…............................ | Cracks, | Inner | All cracks less than 0.20| | | Axial and | Diameter | inch (5.08 mm) in length.| | | Radial | and Outer | | | | Diameter ____All cracks or parts of cracks that are burned |
| NOTE: | | Platforms | or have erosion to a width more than 0.05 inch| | |(Buttresses)| (1.270 mm) are the same as holes. Use the | | |(View D and | burned and broken hole limits. | | | View E) | | | | | Adjacent surfaces of a | | | | | crack or crack connection| | | | | which are at levels that | | | | | are not more than 0.0312 | | | | | inch (0.792 mm) apart. | | | | | | | | | | Connected cracks are per-| | | | | mitted if they do not | | | | | make circular cracks or | | | | | areas where material | | | | | will break off. | | | | ........................................................ | | | Four cracks that are more| Six cracks that are more | | | | than 0.25 inch (6.350 mm)| than 0.25 inch (6.350 mm) | | | | in length in the outer | in length in the outer | | | | diameter platform on the | diameter platform on the | | | | concave airfoil side. | concave airfoil side. | | | | Three cracks not more | Four cracks not more than | | | | than 0.7 inch (17.8 mm) | 0.7 inch (17.8 mm) in | | | | in length. One crack to | length. Two cracks to | | | | any length. These cracks| any length. These cracks | | | | can extend to the airfoil| can extend to the airfoil | | | | concave surface to a | concave surface to a | | | | height of 0.5 inch | height of 0.8 inch | | | | (12.7 mm). | (20.3 mm). | | | ...........................…............................ | | | REMOVE ENGINE WITHIN 5 CYCLES IF EXCEEDANCE OF | | | | REDUCED INTERVAL INSPECTION LIMITS OCCURS, | | | | OR | | | | REMOVE ENGINE IMMEDIATELY IF THERE IS LARGE MATERIAL | | | | LIBERATION. | 2...........…............…......................................................1
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-00-00
ALL ú ú N03 Page 684L 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 | ....................................................…............................
| | | Near each vane, no more | Near each vane, no more |
| | | than two cracks that are | than two cracks that are |
| | | a maximum of 0.60 inch | a maximum of 1.2 inches |
| | | (15.240 mm) in length. | (30.480 mm) in length. |
| | | | |
| | | Follow the given | Follow the given limits |
| | | limits for cracks that | for cracks that go to the |
| | | go to the leading edge | leading edge or the vane |
| | | or the vane airfoil. | airfoil. |
| ........................................…............................ | | Fillet | One crack on each side and two cracks on each vane; | | | Radius | these cracks go along the fillet radius between the | | | between | platform and the vane airfoil. | | | the | | | | Platform | Fillet radius cracks | Fillet radius cracks that | | | and the | that are no more than | are no more than 1.0 inch | | | Vane | 0.6 inch (15.240 mm) | (25.400 mm) in length. | | | Airfoil | in length. | | 2...........…............…..........................…...........................1 | Cracks, | Fillet | Fillet radius cracks that| Fillet radius cracks that | | Axial and | Radius | connect with other | connect with other cracks,| | Radial | between | cracks, if the total | if the total crack length | | | the | crack length is less than| is less than 1.75 inches | | | Platform | 1.0 inch (25.400 mm). | (44.450 mm). | | | and the | | | | | Vane | | Fillet radius cracks that | | | Airfoil | No fillet radius cracks | go to the leading edge | | | | that go to the leading | and are no more than 0.4 | | | | edge. | inch (10.160 mm) in length| 2...........…............…..........................…...........................1
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