....................................................................... | B |All dents are permitted. |Pushed out areas are | | |Pushed out areas on the |caused by dents on the | | |opposite side of the airfoil |opposite side of the | | |are permitted if there are |airfoil surface. | | |no cracks. | | ....................................................................... | C |Damage that is not more than |Nicks in the leading and | | |0.031 inch (0.794 mm) in |trailing edges change the | | |depth is permitted if the |performance of the engine | | |damage is radially apart by |more when they are closer | | |a minimum of 0.25 inch (6.35 |to the blade root. Damage| | |mm). |with small radii or sharp | | | |edges change it the most. | ....................................................................... | D | Small surface erosion is |The small surface erosion | | | permitted. No other damage |will look larger because | | | is permitted. |of borescope magnification| ....................................................................... | E |Damage that is not more than |Nicks in the leading and | | |0.016 inch (0.397 mm) in |trailing edges change the | | |depth is permitted if the |performance of the engine | | |damage is radially apart by |more when they are closer | | |a minimum of 0.25 inch (6.35 |to the blade root. Damage| | |mm). |with small radii or sharp | | | |edges change it the most. | 2............….............................…..........................1 3) Refer to Table 603 for the continue-in-service limits for
 the HPC 9th- thru 12th-stage blades (Fig. 612).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
 72-00-00
 ALL  ú ú N02 Page 680Q ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
No. 15 - HPC Vane and Blade (5th- through 15th-Stage) Inspection
________________________________________________________________
 ~..................................................................... | TABLE 603 | ....................................................................... | HPC 9th- thru 12th-Stage Continue-In-Service Limits | ....................................................................... | BLADE AREA | CONTINUE-IN-SERVICE LIMITS | NOTES | ....................................................................... |Airfoil |Airfoil discoloration and |Discoloration or shiny | |Surfaces |shiny surfaces are |surfaces are not cause | |Both Sides |permitted. |for engine removal. | ....................................................................... | A |Not more than 0.25 inch |Nicks and dents near the | | |(6.35 mm) of a corner can be |leading and trailing edge |
 |  |fully broken off.  Curled,  |corners do not change the |
 |  |different shape, or impact  |engine performance much.  |
 |  |damaged material is  |  |
 |  |permitted.  |  |

 ....................................................................... | B |All dents are permitted. |Pushed out areas are | | |Pushed out areas on the |caused by dents on the | | |opposite side of the airfoil |opposite side of the | | |are permitted if there are |airfoil surface. | | |no cracks. | | ....................................................................... | C |Damage that is not more than |Nicks in the leading and | | |0.031 inch (0.794 mm) in |trailing edges change the | | |depth is permitted if the |performance of the engine | | |damage is radially apart by |more when they are closer | | |a minimum of 0.25 inch (6.35 |to the blade root. Damage| | |mm). |with small radii or sharp | | | |edges change it the most. | ....................................................................... | D | Small surface erosion is |The small surface erosion | | | permitted. Signs of too |will look larger because | | | much heat (blue colors) |of the borescope | | | are permitted on the tip, |magnification. | | | but not on the concave | | | | or convex surfaces. No | | | | other damage is permitted. | | 2............….............................…..........................1 4) Refer to Table 604 for the continue-in-service limits for
 the HPC 13th- thru 15th-stage blades (Fig. 612).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
 72-00-00
 ALL  ú ú N02 Page 680R ú Jun 18/00
　
中國航空網 m.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(65)