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BOLT  OD  0.3730  0.3740  0.3718  X 
12  LINK  *[18]  0.390  0.395  0.430  *[6] 0.55  X 
BUSHING  *[19]  0.356  0.384  0.340  X 
13  BUSHING  ID  2.5000  2.5010  2.5070  0.0062  X  *[20] 
PIN  OD  2.4980  2.4990  2.4948  X  *[1] 
14  BUSHING  ID  2.5000  2.5010  2.5042  0.0062  X  *[21] 
PIN  OD  2.4980  2.4990  2.4948  X  *[1] 
15  BUSHING  ID  2.5000  2.5020  2.5052  0.0072  X  *[22] 
PIN  OD  2.4980  2.4990  2.4948  X  *[1] 
16  PIN  *[23]  8.760  8.785  8.792  0.045  X  *[1] 
BUSHING  *[24]  8.747  8.753  8.740  X  *[25] 
17  BUSHING  *[26]  7.060  7.064  7.074  0.018  X  *[25] 
BUSHING  *[27]  7.038  7.058  7.046  X  *[25] 
18  BUSHING  *[28]  4.702  4.713  4.716  0.018  X  *[25] 
BUSHING  *[29]  4.691  4.700  4.686  X  *[25] 
19  PIN  ID  0.203  0.207  0.220  0.032  X  *[1] 
BOLT  OD  0.1885  0.1895  0.1875  X  *[1] 

Nose Gear Drag Strut Wear Limits
Figure 601 (Sheet 5)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 32-21-04
 ALL  ú ú 01 Page 606 ú Jun 10/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
*[1]  WORN PART IS REPAIRABLE. REFER TO OVERHAUL MANUAL FOR REPAIR INFORMATION. 
*[2]  OBTAIN BUSHING. INSTALL BUSHING IN SUPPORT FITTING WITH BMS 10-11, TYPE 1 PRIMER. DO NOT 
OBSTRUCT GREASE CHANNEL WITH PRIMER. REFER TO 20-11-01. REAM BUSHING TO 3.250 +0.001/-0.000-INCH 
DIAMETER. MACHINE BUSHING ID SURFACE TO 32-MICROINCH FINISH. APPLY FILLET SEAL AROUND SIDE OF 
BUSHING FLANGE. 
*[3]  REFER TO OVERHAUL MANUAL FOR REPLACEMENT INFORMATION. 
*[4]  DIMENSION BETWEEN FLANGES OF BUSHINGS IN SUPPORT FITTINGS. 
*[5]  WIDTH OVER FLANGES OF BUSHINGS IN UPPER DRAG STRUT. 
*[6]  SUMMATION OF GAPS ON BOTH SIDES. 
*[7]  DISTANCE BETWEEN FLANGE OF BUSHING IN ACTUATOR CRANK FITTING AND DOWNLOCK FITTING. 
*[8]  WIDTH OVER OUTER FLANGED BUSHING IN SUPPORT FITTINGS. 
*[9]  DISTANCE BETWEEN FLANGES OF BUSHING PAIR. 
*[10]  WIDTH OVER BEARING. 
*[11]  OBTAIN BUSHING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0004 TO 0.0024 INCH. 
*[12]  OBTAIN BUSHING FOR ACTUATOR CRANK FITTING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 
0.0011 TO 0.0039 INCH. 
*[13]  REPLACE LOCK ACTUATOR. REFER TO 32-34-03. 
*[14]  DIMENSION BETWEEN FLANGES OF BUSHINGS IN DOWNLOCK RELEASE LINK. 
*[15]  LENGTH OF BOLT SHOULDER TO SHOULDER. 
*[16]  WIDTH OVER FLANGES OF BUSHINGS IN DOWNLOCK RELEASE LINK. 
*[17]  OBTAIN BUSHING FOR DOWNLOCK CRANK FITTING. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT 
OF 0.0009 TO 0.0026 INCH. 
*[18]  DISTANCE BETWEEN LINK CLEVIS. 

Nose Gear Drag Strut Wear Limits
Figure 601 (Sheet 6)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 32-21-04
 ALL  ú ú 01 Page 607 ú Jun 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

*[19]  WIDTH OVER FLANGES OF BUSHING IN DOWNLOCK CRANK OR STRUT CLEVIS.
*[20]  OBTAIN BUSHING FOR LOWER DRAG STRUT. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0010 TO 0.0035 INCH. MAXIMUM OVERSIZE HOLE IN STRUT 2.82 INCHES.
*[21]  OBTAIN BUSHING FOR LOWER TRIPOD BRACES. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF 0.0009 TO 0.0033 INCH. MAXIMUM OVERSIZE HOLE IN BRACE 2.81 INCHES.
*[22]  OBTAIN BUSHING FOR UPPER TRIPOD BRACE. INSTALL BUSHING PER 20-11-01 WITH INTERFERENCE FIT OF
　
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