747-400 AMM 飞机维护手册 发动机 ENGINE 1(182)

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____ speed power tool first. Then, blend by hand with an abrasive stone, to make the area smooth.
 (a)  Always blend in a longitudinal direction (parallel with the length of the blade).
 S 328-009-N00
 (2)  Refer to Table 801 and the limits that follow when you repair the damage that you found during the inspection (Fig. 801).
 NOTE:____These limits are a result of structural analysis. The part part life and the performance of the engine can decrease quickly when the damage of the parts becomes near to the maximum continue-in-service limits.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
~............................................................. | MAXIMUM PERMITTED BLEND LIMITS | ............................................................... | BLADE AREA | LIMIT | ............................................................... | A | 0.375 inch (9.525 mm) radius | ...............................................................
 |  B  | Not more than 25% of the local  |
 |  | thickness and not more than  |
 |  | 10% of the airfoil surface  |

 ............................................................... | C | 0.125 inch (3.175 mm) in depth | ............................................................... | D | None | ............................................................... | E | 0.032 inch (0.813 mm) in depth | 2......................…......................................1
 1.6th-Stage Blade Blend Limits Table 801
 NOTE: These limits are for damage that was blended, and not for
____ damage that is not blended.
 (a)  
Blended areas must have a length that is not less than four times the depth.

 (b)  
The limits that follow are for blended areas that are at the maximum depth on opposite edges of the blades. 1) One blended area must not be immediately opposite the

 other. 2) One blended area must not be less than the average blade width from the other blended area.

 (c)  
No more than two blended areas at the maximum depth limit are permitted on each blade edge.

 (d)  
All blended edge damage which is not more than 1/2 the maximum depth limit are permitted, if 3/4 of each edge is not blended.

 (e)  
The sum of the lengths of blended tip damage must not be more than 25% of the total tip length.

 (f)  
On smooth, rounded bottom dents, remove only the edge of the damage.

 (g)  
Repair defects that are on the inner half of the blade only after you carefully examine them.

 NOTE: Nicks in the leading and trailing edges change the
____ performance of the engine more when they occur near to the root.
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 ALL  ú ú N01 Page 804 ú Feb 10/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
S 238-010-N00
 (3)  
With ultra high sensitivity penetrant, do a fluorescent penetrant inspection of the repaired areas of the blades (AMM 70-31-01/201).

 (a)  
No cracks are permitted.

 G.
Put the Airplane Back to Its usual Condition.

 S 418-011-N00
 (1)  
Install the 1st-stage stator (AMM 72-31-04/401).

 S 098-012-N00

 (2)
Remove the protective mat from the inner surface of the fan case.

 S 418-013-N00

 (3)  
Install all of the 1st-stage fan blades (AMM 72-31-02/401).

 S 418-014-N00

 (4)  
Install the inlet cone (AMM 72-31-01/401).

 S 098-015-N00

 (5)
Remove the protective mat from the inner surface of the inlet cowl.

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