曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

 |  |  |  a) There is only one  |  a) There is only one  |
 |  |  |  crack.  b) The crack  |  crack.  b) The crack  |
 |  |  |  is no more than 1.25  |  is no more than 2.50  |
 |  |  |  inches (32.75 mm) in  |  inches (63.5 mm) in  |
 |  |  |  length.  c) The crack |  length.  |
 |  |  |  does not go around the|  (It can go around  |
 |  |  |  leading edge.  |  the leading edge.)  |

 | ................................................................... | |Leading Edge |1. A radial crack on, or |1. A radial crack on, or | | |Area of the | adjacent to, the lead-| adjacent to, the lead-| | |Strut | ing edge weld of the | ing edge weld of the | | | | strut is permitted if:| strut is permitted if:| | | | a) The crack does not | a) The crack is no | | | | go into the I.D. or | more than 2.50 inches | | | | O.D. of the fillet ra-| (63.5 mm) in length. | | | | dius. b) The crack is| | | | | no more than 1.25 | (It can go through | | | | inches (31.75 mm) in | the fillet radius.) | | | | length. | | | | ..................................................... | | |2. The maximum permitted |2. The maximum permitted | | | | length of an axial | length of an axial | | | | crack or a crack in | crack or a crack in | | | | the direction of a | the direction of a | | | | chord (that goes | chord (that goes | | | | through the leading | through the leading | | | | edge to the airfoil | edge to the airfoil | | | | surface) is 1.25 | surface) is 2.5 inches| | | | inches (31.75 mm). | (63.5 mm). | | ...................................................................
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
~.............................................................................. | TABLE 602 | ................................................................................ | | | GASPATH AREA OF THE TURBINE EXHAUST CASE | | | | CONTINUE-IN-SERVICE LIMITS | | | ..................................................... | CONDITION | | | | | FOUND | INSPECTION | REGULAR | DECREASED | | (FIG. 602) | AREA | TIME INSPECTION | TIME INSPECTION | ................................................................................ | |Strut Trail- |1. No more than three |1. No more than three | | |ing Edge Area| cracks longer than | cracks longer than | | | | 0.75 inch (19.05 mm) | 1.25 inches (31.75 mm)| | | | are permitted on a | are permitted on a | | | | strut. | strut. Only one crack| | | | | longer than 1.75 | | | | | inches (44.45 mm) is | | | | | permitted. | | | ..........................….......................... | | |2. No semicircular cracks or areas where material | | | | will break off are permitted. | | | ..................................................... | | |3. Radial cracks that |3. Radial (in the direc- | | | | are no more than 1.25 | tion of the span) and | | | | inches (31.75 mm) in | axial (in the direc-| | | | length are permitted. | tion of a chord) | | | | | cracks no longer than | | | | | 2.5 inches (63.5 mm) | | | | | are permitted on the | | | | | airfoil area. | | | ..................................................... | | |4. Axial cracks that go |4. Cracks that go through| | | | through the airfoil to| the fillet radius or | | | | the leading edge that | the leading edge are | | | | are no longer than | permitted. | | | | 1.25 inches (31.75 mm)| | | | | are permitted. | | | | ..................................................... | | |5. Cracks that go into |5. The total sum of the | | | | the leading edge or | lengths of all cracks | | | | the fillet radius are | is not permitted to be| | | | permitted. | more than 5.0 inches | | | | | (127.0 mm). | | | .....................................................
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
~.............................................................................. | TABLE 602 | ................................................................................ | | | GASPATH AREA OF THE TURBINE EXHAUST CASE | | | | CONTINUE-IN-SERVICE LIMITS | | | ..................................................... | CONDITION | | | | | FOUND | INSPECTION | REGULAR | DECREASED | | (FIG. 602) | AREA | TIME INSPECTION | TIME INSPECTION | ................................................................................ | | |6. All cracks that are | | | | | less than 0.75 inch | | | | | (19.05 mm) in length, | --------| | | | that are confined to | | | | | the airfoil area only,| | | | | are permitted. | | 2............….............….........................….........................1
　
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