72-54-01
ALL ú ú N02 Page 608 ú Oct 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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 | ................................................................................
|Cracks |Inner and |1. Circumferential or |1. Circumferential or |
| |Outer Duct | axial cracks with a | axial cracks with a |
| |Areas | maximum length of 1.25| maximum length of 2.50|
| | | inches (31.75 mm) are | inches (63.50 mm) are |
| | | permitted. | permitted. |
| | ..........................…..........................
| | |2. A continuous crack of no more than two intersec-|
| | | ting cracks between any two struts are counted |
| | | as one crack. |
| | .....................................................
| | |3. No semicircular cracks or areas where material |
| | | will break off are permitted. |
| | .....................................................
| | |4. A maximum of three |4. A maximum of three |
| | | cracks more than 0.75 | cracks more than 1.25 |
| | | inch (19.05 mm) in | inches (31.75 mm) in |
| | | length are permitted | length are permitted |
| | | between two adjacent | between two adjacent |
| | | struts. | struts. |
| | ..........................…..........................
| | |5. All cracks that are less than 0.75 inch |
| | | (19.05 mm) in length, that are confined to the |
| | | duct area only, are permitted. |
| ................................................................... | |Struts |1. Radial cracks that go |1. Radial cracks that go | | | | through the fillet ra-| through the fillet ra-| | | | dius on one strut are | dius on one strut are | | | | permitted if: a) Each| permitted if: a) Each| | | | crack is no more than | crack is no more than | | | | 1.25 inches (31.75 mm)| 2.50 inches (63.5 mm) | | | | in length. b) There | in length. b) There | | | | are no more than two | are no more than two | | | | cracks. This includes| cracks. This includes| | | | all parts of the crack| all parts of the crack| | | | that are on the air-| that are on the air-| | | | foil or duct surfaces.| foil or duct surfaces.| | | .....................................................
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72-54-01
ALL ú ú N01 Page 609 ú Oct 10/95
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 | ................................................................................
| | |2. An axial crack along |2. An axial crack along |
| | | the airfoil I.D. or | the airfoil I.D. or |
| | | O.D. weld line on one | O.D. weld line on one |
| | | strut is permitted if:| strut is permitted if:|
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