(a)  
Remove the material as necessary with the PWA 29914 Cutter to form the 10 degree angle.

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////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////

PLANE Z
(P/N 56A821)
L-A6147 L-B1525
Leading Edge Contour Repair Figure 808 (Sheet 1)
H18968
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7
PLANE Z
(P/N 56A621)
L-A6147 L-B1525
Leading Edge Contour Repair Figure 808 (Sheet 2)
H75257
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
INDEX  P/N 56A821 BLADES  P/N 56A621 BLADES 
1  THICKNESS WITHIN INDEX 1 IS NOT TO BE LESS THAN THE ACTUAL MAKE SMOOTH BETWEEN ZONES J AND K WITHIN INDEX 1. MINIMUM OF ADJACENT ZONE ABOVE PLANE V. THICKNESS OF LEADING EDGE AT LOCATION DA (VIEW A-A, ZONE J) 
2  (596.0-602.4 mm) 23.465-23.715 INCHES  22.609-22.859 INCHES (574.3-580.6 mm) 
3  ABOVE PLANE X. THICKNESS OF LEADING EDGE AT LOCATION DE OF ADJACENT ZONE THICKNESS WITHIN INDEX 3 IS NOT TO BE LESS THAN THE ACTUAL MAKE SMOOTH BETWEEN ZONES K AND L WITHIN INDEX 3. MINIMUM 
4  (615.1-621.4 mm) 24.215-24.465 INCHES  23.609-23.359 INCHES (599.7-593.3 mm) 
5  (198.4-204.8 mm) 7.812-8.062 INCHES  7.812-8.062 INCHES (198.4-204.8 mm) 
6  8.562-8.812 INCHES (217.5-223.8 mm)  8.562-8.812 INCHES (217.5-223.8 mm) 
7  TANGENT OF PLATFORM ROOT FILLET RADIUS 

Leading Edge Contour Repair
Figure 808 (Sheet 3)

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H18970
0.025-0.031 INCH (0.635-0.787 mm)

AIRFOIL SECTION PROFILE
0.041-0.047 INCH EXAMPLE SECTION OVER ZONE J (1.042-1.193 mm)

EXAMPLE SECTION OVER ZONE K 
B-B 
CHAMFER IF NECESSARY TO 
MAINTAIN THIS DIMENSION 
FROM PLANE M TO PLANE X.  L-A6148 

Leading Edge Contour Repair
Figure 808 (Sheet 4)

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H75261
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0.007 INCH

(1.016 mm) 4
E-E
THIS RADIUS MUST BE BLENDED SMOOTHLY WITH REMAINDER OF AIRFOIL CONTOUR.
BLEND SMOOTHLY WITHIN REMAINDER OF AIRFOIL SECTION. PROFILE THICKNESS IN ZONE P MUST NOT BE LESS THAN THICKNESS MEASURED AT LOCATIONS Q OR R AS APPLICABLE.
MEASURE THICKNESS AT THIS DIMENSION.  L-A6148

Leading Edge Contour Repair
Figure 808 (Sheet 5)

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