72-31-04
 ALL  ú
 ú  N01  Page 602
 ú  Jun 10/93 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.

C-C  D-D

1st-Stage Stator Inspection
Figure 601 (Sheet 2)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
C17243
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
E. Examine the 1st-Stage Stator Vanes (Fig. 601).
 S 236-003-N00
 (1)  
With high sensitivity penetrant, do a fluorescent penetrant
 inspection of the 1st-stage stator vanes for cracks
 (AMM 70-31-01/201).

 (a)  
Cracks are not permitted.

 S 226-004-N00
 (2)  
Replace or repair vanes that have nicks or dents (AMM 72-31-04/801).

 S 226-007-N00

 (3)  
Compare the damage you find with Table 601 and the limits that follow.

 NOTE: These limits are for damage that was blended, and not for
____
 damage that is not blended.

 ~................................................ | Table 601 | | 1st-Stage Stator Blend Limits | .................................................. | MAXIMUM ALLOWABLE BLEND LIMITS | .................................................. | VANE AREA | LIMIT | .................................................. | A | 0.100 inch (2.540 mm) | .................................................. | B | 0.090 inch (2.286 mm) | .................................................. | C | 0.100 inch (2.540 mm) | .................................................. | D | 0.090 inch (2.286 mm) | .................................................. | E | 25 percent of local thickness | 2...........…....................................1
 (a)  
Blended areas on the concave airfoil surface can be on no more than 20 percent of its surface area. 1) Round bottom dents are permitted.

 (b)  
Blended areas on the convex airfoil surface can be on no more than 5 percent of its surface area.

 (c)  
The sum of the lengths of all blended areas on the two edges of a vane must not be more than 0.500 inch (12.700 mm).

 (d)  
No more than two blended areas at the maximum depth limit are permitted on each vane.

 (e)  
Areas that are blended must have a radial length that is not less than four times the depth.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
(f)  
The limits that follow are for blended areas that are at the maximum depth on opposite edges of the vane. 1) One blended area must not be immediately opposite the

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

 (g)  
The limit that follows is for blended areas that are not at the maximum depth, are on opposite edges, and one is nearer than the average vane width to the other. 1) The sum of the depths on the two blended areas must not be

 more than the maximum depth for one blended nick.

 (h)  
The sum of the lengths of all edge blended areas on the vane and shroud assembly must not be more than 6.000 inches

 (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 tha 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.

 (m)  
Compare the damage to the sealing compound on the inner shroud with the limits that follow (Fig. 601, View C): 1) Very small cracks (called crazing), dryness, and areas
　
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