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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
H75264
SURFACE E
INDEX 8 INDEX 9
0.0021 INCH 0.0162 INCH
(0.053 mm) (0.411 mm)
0.0074 INCH 0.0202 INCH
(0.188 mm) (0.513 mm)
0.0168 INCH 0.0251 INCH
(0.427 mm) (0.638 mm)
0.0263 INCH 0.0290 INCH
(0.688 mm) (0.737 mm)
0.0359 INCH 0.0323 INCH
(0.912 mm) (0.820 mm)
0.0456 INCH 0.0352 INCH
(1.158 mm) (0.894 mm)
0.0553 INCH 0.0378 INCH
(1.405 mm) (0.960 mm)
0.0651 INCH 0.0401 INCH
(1.654 mm) (1.019 mm)
0.0749 INCH 0.0422 INCH
(1.902 mm) (1.072 mm)
0.0862 INCH 0.0443 INCH
(2.1.89 mm) (1.125 mm)
SURFACE F
INDEX 8 INDEX 9
(1.008 mm) 0.0397 INCH (0.785 mm) 0.0309 INCH (0.523 mm) 0.0206 INCH (0.259 mm) 0.0102 INCH (0.099 mm) 0.0039 INCH (0.0000 mm) 0.0000 INCH 0.0002 INCH 0.0009 INCH 0.0027 INCH 0.0048 INCH (0.051 mm) (0.023 mm) (0.069 mm) (0.122 mm)
SURFACE G
INDEX 11 INDEX 10
0.0087 INCH 0.0274 INCH
(0.221 mm) (0.696 mm)
0.0129 INCH 0.0290 INCH
(0.328 mm) (0.737 mm)
0.0225 INCH 0.0323 INCH
(0.572 mm) (0.820 mm)
0.0322 INCH 0.0352 INCH
(0.818 mm) (0.894 mm)
0.0419 INCH 0.0378 INCH
(1.064 mm) (0.960 mm)
0.0517 INCH 0.0401 INCH
(1.313 mm) (1.019 mm)
0.0615 INCH 0.0422 INCH
(1.562 mm) (1.072 mm)
0.0728 INCH 0.0443 INCH
(1.849 mm) (1.125 mm)
SURFACE H
INDEX 11 INDEX 10
0.0263 INCH (0.668 mm) (0.444 mm) 0.0175 INCH (0.333 mm) 0.0131 INCH (0.000 mm) 0.0000 INCH (0.0051 mm) 0.0002 INCH (0.010 mm) 0.0004 INCH
L-A6149
Leading Edge Contour Repair Figure 808 (Sheet 6)
H75265
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72-31-02
ALL ú
ú N01 Page 827
ú Oct 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
L-A4428
PLANE Z
INDEX LIMIT
1 10.545-10.795 INCHES (267.8-274.2 mm)
2 TRANSITION IN THIS AREA MUST BE BLENDED SMOOTHLY. MINIMUM THICKNESS IN THIS AREA IS NOT TO BE LESS THAN THE ACTUAL THICKNESS OF THE LEADING EDGE AT LOCATION Q IN ZONE J.
3 9.795-10.045 INCHES (248.8-255.1 mm)
4 TRANSITION IN THIS AREA MUST BE BLENDED SMOOTHLY. MINIMUM THICKNESS IN THIS AREA IS NOT TO BE LESS THAN THE ACTUAL THICKNESS OF THE LEADING EDGE AT LOCATION R IN ZONE K.
5 4.100-4.350 INCHES (104.1-110.5 mm)
6 4.850-5.100 INCHES (123.2-129.5 mm)
Leading Edge Contour Repair (PN 52A121 Blades)
Figure 809 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
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ALL ú ú N01 Page 828 ú Oct 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
H18992
B-B
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-A4429
0989
Leading Edge Contour Repair (PN 52A121 Blades)
Figure 809 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747-400 AMM 飞机维护手册 发动机 ENGINE 1(168)
