72-31-02
ALL ú ú N01 Page 809 ú Oct 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
ORIGINAL
SEE
NEW CONTOUR
ORIGINAL CONTOUR
TRAILING EDGE B-B L-A2320
1.
1.000 INCH (25.400 mm) - YOU CAN BLEND DAMAGE ONLY IN THE PLATFORM TO LEADING OR TRAILING EDGE
RADIUS TO A MAXIMUM DEPTH OF INDEX 2.
2.
BLEND REPAIRS ON THE LEADING OR TRAILING EDGE MUST NOT BE MORE THAN 0.150 INCH (3.810 mm) IN DEPTH.
3.
WHEN YOU BLEND DAMAGE IN THIS AREA ADJACENT TO THE PLATFORM, MAKE THE EDGES ROUNDED WITH A RADIUS OF INDEX 5. DO NOT UNDERCUT THE RADIUS OF THE AIRFOIL PLATFORM FILLET WHEN YOU BLEND DAMAGE ADJACENT TO THE PLATFORM.
4.
0.359-0.391 INCH (9.12-9.93 mm) RADIUS
5.
0.030-0.050 INCH (0.76-1.27 mm) RADIUS
6.
0.000-0.020 INCH (0.00-0.51 mm) VERTICAL TO (MEASURE AT 90` FROM) THE PLATFORM.
7.
THE CHORD LENGTH MUST NOT BE LESS THAN 6.950 INCHES (176.53 mm) IN THE AREA 6.300 INCHES (160.02 mm) FROM THE LEADING EDGE PLATFORM. THE CHORD LENGTH MEASUREMENT MUST BE MEASURED TANGENT TO THE BLADES LEADING AND TRAILING EDGES AND LEVEL WITH PLANE Z.
8.
MAKE THE RADIUS OF THE BLEND REPAIR EQUAL TO HALF OF THE EDGE THICKNESS. IF THE RADIUS IS MORE THAN
O.062 INCH (1.575 mm) SEE INDEX 10 FOR THE BLEND LIMITS.
9.
KEEP THE EDGE THICKNESS IN THE MINIMUM THICKNESS LIMITS IN FIG. 801.
10.
0.130-0.190 INCH (3.30-4.83 mm). BLEND THE RADIUS AT INDEX 8. WITH A HAND FILE AND AN EMERY CLOTH MAKE THIS AREA SMOOTH ON EACH SIDE OF THE AIRFOIL.
Leading and Trailing Edge Root Blend Limits
Figure 805 (Sheet 1)
H75220
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-31-02
ALL ú
ú N01 Page 810
ú Oct 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
ORIGINAL
SEE
NEW CONTOUR
ORIGINAL CONTOUR
TRAILING EDGE D-D L-A2320
1.
1.000 INCH (25.400 mm) - YOU CAN BLEND DAMAGE ONLY IN THE PLATFORM TO LEADING OR TRAILING EDGE
RADIUS TO A MAXIMUM DEPTH OF INDEX 2.
2.
BLEND REPAIRS ON THE LEADING OR TRAILING EDGE MUST NOT BE MORE THAN 0.150 INCH (3.810 mm) IN DEPTH.
3.
WHEN YOU BLEND DAMAGE IN THIS AREA ADJACENT TO THE PLATFORM, MAKE THE EDGES ROUNDED WITH A RADIUS OF INDEX 5. DO NOT UNDERCUT THE RADIUS OF THE AIRFOIL PLATFORM FILLET WHEN YOU BLEND DAMAGE ADJACENT TO THE PLATFORM.
4.
0.359-0.391 INCH (9.12-9.93 mm) RADIUS
5.
0.030-0.050 INCH (0.76-1.27 mm) RADIUS
6.
0.000-0.020 INCH (0.00-0.51 mm) VERTICAL TO (MEASURE AT 90` FROM) THE PLATFORM.
7.
THE CHORD LENGTH MUST NOT BE LESS THAN 6.950 INCHES (176.53 mm) IN THE AREA 6.300 INCHES (160.02 mm) FROM THE LEADING EDGE PLATFORM. THE CHORD LENGTH MEASUREMENT MUST BE MEASURED TANGENT TO THE BLADES LEADING AND TRAILING EDGES AND LEVEL WITH PLANE Z.
8.
MAKE THE RADIUS OF THE BLEND REPAIR EQUAL TO HALF OF THE EDGE THICKNESS. IF THE RADIUS IS MORE THAN
O.062 INCH (1.575 mm) SEE INDEX 10 FOR THE BLEND LIMITS.
9.
KEEP THE EDGE THICKNESS IN THE MINIMUM THICKNESS LIMITS IN FIG. 801.
10.
0.130-0.190 INCH (3.30-4.83 mm). BLEND THE RADIUS AT INDEX 8. WITH A HAND FILE AND AN EMERY CLOTH MAKE THIS AREA SMOOTH ON EACH SIDE OF THE AIRFOIL.
Leading and Trailing Edge Root Blend Limits
Figure 805 (Sheet 2)
H75221
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-31-02
ALL ú
ú N01 Page 811
ú Oct 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
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