(152.4 mm).
 (i)  
All local blended areas on the concave and convex sides must have an area that is not less than 15 times the depth of the damage.

 (j)  
Pitting and corrosion can be repaired if the damage does not have a depth that is more than 12 percent of the local vane thickness.

 NOTE: Pitting is a concentration of corrosion at a point.
____
 (k)  
The Surface finish on a blended vane must be the same as the surface finish on a new vane.

 (l)  
Damage, which you can see on the opposite side of the vane is not permitted.

 S 238-003-N00
 (4)  
With high sensitivity penetrant, do a fluorescent penetrant inspection on the blended vanes (AMM 70-31-01/201) to make sure that all damage is repaired.

 (a)  
Replace the vane if you find a crack.

 G.  
Put the Airplane Back to its Usual Condition.

 S 418-005-N00
 (1)  
Install the 1st-stage stator (AMM 72-31-04/401).

 S 098-006-N00

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

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

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

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

 S 418-007-N00
 S 418-008-N00
 S 098-009-N00
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 72-31-04
 ALL  ú ú N01 Page 805 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
1.6TH-STAGE BLADE - INSPECTION/CHECK
____________________________________
 1.  General
_______
 A.  This procedure gives the steps for the inspection of the 1.6th-stage blades.
 B.  The 1.6th-stage blades are immediately aft of the 1st-stage stator of the low pressure compressor (LPC).
 C.  To get access to the 1.6th-stage blades for the inspection, you must remove the inlet cone, the 1st-stage fan blades, and the 1st-stage stator.
 TASK 72-31-05-206-001-N00
 2.  Examine the 1.6th-Stage Blades
______________________________
 A.  General
 (1)  
It is necessary to examine the 1.6th-stage blades only if the inspection of the 1st-stage stator showed damage.

 (2)  
Damaged areas that were made smooth for a repair are referred to as blended areas.

 B.  
References

 (1)  
AMM 70-31-01/201, Fluorescent Penetrant Inspection

 (2)  
AMM 72-31-01/401, Inlet Cone

 (3)  
AMM 72-31-02/401, 1st-Stage Fan Blades

 (4)  
AMM 72-31-04/401, 1st-Stage Stator

 (5)  
AMM 72-31-05/801, 1.6th-Stage Blade

 (6)  
AMM 72-31-08/601, 1.6th-Stage Stator Rubstrip

 (7)  
IPC 72-31-05 Fig. 1

 C.  
Access

 (1)  
Location Zone
 412 Engine 1 - LPC
 422 Engine 2 - LPC
 432 Engine 3 - LPC
 442 Engine 4 - LPC

 D.  
Procedure

 (1)  
Remove the inlet cone (AMM 72-31-01/401).

 S 016-007-N00
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 72-31-05
 ALL  ú ú N01 Page 601 ú Jun 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////

FAN EXIT FAIRING

L-A0909
A-A
MINIMUM DISTANCE BETWEEN BLEND REPAIRS ON OPPOSITE EDGES MUST NOT BE LESS THAN THE AVERAGE BLADE WIDTHL-A0616
MINIMUM DISTANCE BETWEEN BLEND REPAIRS
LEADING EDGE
APPROXIMATE
AREAS C AND E

AREAS C AND E
DEPTH DIMENSION
B-B
BLEND REPAIR EDGE DAMAGE
AREA B AREA D
AREA

AREA C L-A0910 1.6th-Stage Blade Inspection Figure 601
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
　
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(179)