| | INNER AND OUTER COMBUSTION CHAMBER ASSSEMBLY (Except Bulkhead)|
| | CONTINUE-IN-SERVICE LIMITS |
| CONDITION .................................................................
| FOUND | PERMITTED WITH REGULAR | PERMITTED WITH DECREASED |
| FIGURE 619 | TIME INSPECTION | TIME INSPECTION |
................................................................................. | Circumferen-| Only cracks in the lip area are permitted. The maximum | | tial Cracks | length for the lip cracks is 2.0 inches (50.800 mm). | ................................................................................. | Connection of | The only cracks permitted are in the lip area. | | Axial and | | | Circumferen-| Louver lip material that is missing because of the connection | | tial Cracks | of axial and circumferential cracks is permitted. | ................................................................................. | Connection of | Refer to the limits for Burn-Through (Open Holes) and Axial | | Axial Cracks | Cracks. Include the width of the burn hole as part of the | | and Burned | total crack length. | | Holes | | 2...............…...............................................................1
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72-00-00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
~...............................................................................
| | TABLE 607 |
.................................................................................
| | COMBUSTION CHAMBER ASSEMBLY BULKHEAD AND |
| | FUEL INJECTOR GUIDE HEATSHEILD |
| | CONTINUE-IN-SERVICE LIMITS |
| CONDITION ............................................................... ..
| FOUND | PERMITTED WITH REGULAR | PERMITTED WITH DECREASED |
| FIGURE 617 | TIME INSPECTION | TIME INSPECTION |
................................................................................. | Cracks in the | All quantities of cracks that are not more than 0.25 inch | | Heatshield | (6.350 mm) in length are permitted. | | Face | | | | Cracks that go through other cracks are not permitted. | | | | | | No more than two cracks that | No more than four cracks that | | | are longer than 0.25 inch | are longer that 0.25 inch | | | (6.350 mm) are permitted. | (6.350 mm) are permitted. | | | | | | | Two cracks on each face are | Four cracks on each face are | | | permitted to go across each | permitted to go across each | | | face, but must be apart by | face, but must be apart by | | | at least 45°. | at least 30°. | ................................................................................. | Erosion of | All quantities of erosion of | All quantities of erosion of | | the Inner | the Inner Heatshield Face are | the Inner Heatshield Face are | | Heatshield | permitted. But, the imping-| permitted. But, no more than | | Face (Material| ment holes must not be open | four impingment holes on each | | that is | to view from the rear. | Heatshield are permitted to | | missing) | | be open to view from the rear.| ................................................................................. | Erosion of the| Outer Heatshield Face Erosion | Erosion which extends from the| | Outer Heat. | must not extend more than | perimeter of the Outer Heat-| | shield Face | 0.200 inch (5.080 mm) from | shield Face must be more than | | (Material that| the perimeter of the Outer | 0.025 inch (0.635 mm) away | | is missing) | Heatshield Face. | from the Inner Heatshield Face| ................................................................................. | Burned Marks | Heatshield burned marks and distortion are permitted if the | | and Distortion| Heatshield face erosion and cracks are in the limits. The | | in the Heat-| damage that results to the Bulkhead must not be more than | | shield Face | the given limits. | ................................................................................. | Heatshield | All quantities. | | Surface Layer | | | that is | NOTE: | 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：747-400 AMM 飛機維護手冊 發動機 ENGINE 1(75)
