................................................................................ | Nicks and | A | None | On each blade, one nick | | Dents | | | or dent that is not more | | | | | than 0.05 inch (1.27 mm) | | | | | in length or diameter. | | ............................................................... | NOTE: No crack| B |
____| On each blade, one nick| On each blade, one nick | that is with a | | or dent that is not | or dent that is not more | | nick or dent is| | more than 0.05 inch | than 0.08 inch (2.032 mm)| | permitted, | | (1.27 mm) in length or | in length or diamter. | | unless it is | | diameter. | | | in the limits ............................................................... | for Axial or | C | All nicks or dents that| All nicks or dents that | | Radial Cracks. | | are not more than 0.08 | are not more than 0.125 | | | | inch (2.032 mm) in | (3.175 mm) in length or | | | | length or diameter. | diameter. | | | | | | ....................................................…........................... | Surface Layer | A, B | One defect on each blade, in these limits: | | Deterioration, | | 1) Surface layer deterioration on the airfoil no | | Burned Areas | | more than 0.750 inch (19.050 mm) in diameter, | | Erosion | | 0.442 square inch (285 square mm) in area, or | | | | 2) Leading edge burned areas no more than 0.400 | | | | inch (10.160 mm) in diameter, 0.126 square | | | | inch (81 square mm) in area. | | ............................................................... | | C | Same as A, B | One defect on each blade | | | | | if it is in the burned or| | | | | broken hole limits. | ....................................................…...........................
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
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| TABLE 611 |
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| | | 2ND-STAGE HPT BLADE |
| | | CONTINUE-IN-SERVICE LIMITS |
| CONDITION | .....................................................
| FOUND | BLADE | PERMITTED WITH REGULAR | PERMITTED WITH DECREASED |
| FIGURE 624 | AREA | TIME INSPECTIONS | TIME INSPECTIONS |
................................................................................ | Axial or | A | None. | | Radial Cracks | | IMMEDIATELY REMOVE THE ENGINE. | | ............................................................... | NOTE:____If | B | None | All cracks that are less | | there are | | | than 0.130 inch (3.3mm) | | holes, see | | | in length and not with | | "Holes that | | | broken holes and do not | | are Broken or | | | connect with other | | Burned through | | | cracks. | | to the Internal............................................................... | Space", below. | C | All cracks that are | All quantities | | | | not with broken holes | | | Material tears | | and do not connect | | | are the same | | with other cracks. | | | as cracks. | | | | 2................….........…........................…..........................1 | Holes that are | A, B | None | | Broken or | | IMMEDIATELY REMOVE THE ENGINE | | Burned through | | | | to the Internal............................................................... | Space | C | None | On each blade, one piece | | | | | that is missing from the | | | | | 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. | ....................................................…........................... | Bent | C | A bent tip is permitted if the damage is not more | | Tip | | than other damage limits. | ................................................................................ | Blocked Cooling| A | One blocked trailing edge exit slot on each blade.| | Air Exit Slots ............................................................... | in the | B, C | Two isolated, blocked trailing edge exit slots on | | Trailing Edge | | each blade. | ................................................................................ | Tip Rub or | C | All quantities, if it is not worn through to the | | Plasma Spray | | internal cavity. | | Deterioration | | | ................................................................................ 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747-400 AMM 飞机维护手册 发动机 ENGINE 1(90)
