HOLE
L-A7732 (0000) 1st-Stage HPT Blade Continue-In-Service Limits
E24544
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72-00-00
ú ú N01 Page 684Q ú Oct 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
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| TABLE 610 |
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| | | 1ST-STAGE HPT BLADE |
| | | CONTINUE-IN-SERVICE LIMITS |
| CONDITION | .....................................................
| FOUND | BLADE | PERMITTED WITH REGULAR | PERMITTED WITH DECREASED |
| FIGURE 622 | AREA | TIME INSPECTION | TIME INSPECTION |
................................................................................ | Nicks and | A | None | On each blade, one nick | | Dents | | | or dent that is no more | | | | | than 0.08 inch (2.032 mm)| | NOTE:____No crack| | | in length or diameter. | | that is with a ............................................................... | nick or dent is| B | All nicks or dents | All nicks or dent that | | permitted, | | that are not more than | are not more than 0.125 | | unless it is | | 0.08 inch (2.032 mm) | inch (3.175 mm) in length| | in the limits | | in length or diameter. | or diameter. | | for Axial or | | | | | Radial Cracks. | | | | ....................................................…........................... | Burned Areas | A, B, | Burned areas are not | Burned areas to a maximum| | | and C | permitted. | of 0.750 inch (19.050 mm)| | NOTE: Burned | | | in diameter or 0.422 |
____ | areas that | | | square inch (285.0 square| | cause a | | | mm) in area. | | decrease in the| | | Leading edge burned areas| | flow of cooling| | | to a maximum of 0.40 inch| | air is not | | | (10.160 mm) in diameter | | permitted. | | | or 0.126 square inch | | | | | (81.0 square mm) in area.| ................................................................................ | Erosion damage | A, B, | All quantities are | All quantities are | | on the surface | and C | Permitted. | permitted. | | layer. | | | | ................................................................................
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72-00-00
ALL ú ú N01 Page 684R ú Oct 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
~.............................................................................. | 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| A | None | One hole to hole crack on| | Cracks | | | the leading edge only. | | | | | No airfoil cracks. | | NOTE:_____See the | | | | | subsequent | | | NOTE: REMOVE ENGINE |
____ | limits for open| | | IMMEDIATELY IF THERE IS | | cracks. | | | IMMINENT PART FAILURE OR | | Material tears | | | IMMINENT MATERIAL | | are the same | | | LIBERATION. | | as cracks. | | | | | | | | REMOVE ENGINE WITHIN 5 | | | | | CYCLES IF ANY REDUCED | | | | | INTERVAL INSPECTION | | | | | LIMITS ARE E CEEDED. | | ...............................................................
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