Nose Gear Drag Brace Wear Limits 501
32-21-21 Figure 601 (Sheet 1) Aug 15/72
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
501 Nose Gear Drag Brace Wear Limits
Oct 20/92 Figure 601 (Sheet 2) 32-21-21
Page 603
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Nose Gear Drag Brace Wear Limits 501
32-21-21 Figure 601 (Sheet 3) Oct 20/92
Page 604
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
*[1] Worn part or assembly repairable. Refer to Overhaul Manual for repair instructions.
*[2] Install bushings with corrosion preventive compound on faying surfaces and with interference fit of 0.0003 to 0.0016 inch. Machine bushings to design limits with 32-microinch finish. Maximum oversize bushing and hole in fitting is 0.4980 inch, if required.
*[3] Replace link.
*[4] Install bushings with primer on mating surfaces and with interference fit of 0.0005 to 0.0023 inch. Machine bushing to design limits with 32-microinch finish. Dimension between flange faces to be
1.091 to 1.093 inch with 0.060-inch minimum flange thickness.
*[5] Install bushings with grease on faying surfaces and with interference fit of 0.0005 to 0.0023 inch. Machine bushings to design limits with 32-microinch finish. Dimension between flange faces on inside of clevis to be 2.860 to 2.862 inches. Dimension over flange faces of bushing on each clevis is
0.640 to 0.642 inch. Maximum oversize bushing and hole in fitting is 1.000 inch. *[6] Replace lower drag brace. *[7] Install bushings with grease on faying surfaces and with interference fit of 0.0005 to 0.0023 inch.
Machine bushings to design limits with 32-microinch finish in bushing bore. Dimension between bushing flange faces is to be 1.094 to 1.096 inches and parallel within 0.005 inch with a 63-microinch finish. Maximum oversize bushing and hole in strut is 1.4980 inches.
*[8] Used with upper drag brace part number 65-46232-1 *[9] Used with upper drag brace part number 65-46232-3
501 Nose Gear Drag Brace Wear Limits
Aug 15/72 Figure 601 (Sheet 4) 32-21-21
Page 605
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
NOSE GEAR TORSION LINKS - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Ground Lock Assemblies (Ref 32-00-01)
B. Grease - MIL-G-21164 or MIL-G-23827 optional to BMS 3-33 (Ref 20-30-21)
C. Naphtha - P-D-680 solvent (Ref 20-30-21)
D. Corrosion Preventive Compound - MIL-C-11796, Class 3 (Ref 20-30-21)
2. Remove Torsion Links (Fig. 401)
A. Install ground lock assemblies (Ref 32-00-01).
B. Jack airplane nose until nose gear wheels clear the ground (Ref Chapter 7, Jacking
Airplane).Lower tail support jack as nose is raised.
C. Disconnect wire harness (11) from torsion links (3) and (10) (Details B and D.)
(1)
Remove two block clamps (12) to free wire harness from lower torsion link. Remove wire clamp from piston position spring cartridge (27).
(2)
Disconnect lower rod end (26) of piston position spring cartridge from upper torsion link.
NOTE: Wire clamp (22) will become detached from the upper torsion link when rod end of cartridge is disconnected.
(3)
Tape loosened wire harness to shock strut.
D. Remove both nose gear wheels (Ref 32-45-21 Removal/Installation).
E. Jack nose gear axle to relieve any strain on torsion links.
554
Sep 01/02 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-21-31 Page 401
F. Remove apex bolt (18) to disconnect torsion links (detail C).
(1)
Remove cotter pin (20) from nut on apex bolt.
(2)
Remove nut, thrust bearing (21), bushing (21A), and apex bolt.
NOTE: A thin washer between torsion links will be free for removal when apex bolt is removed.
(3)
Remove thin washer (19).
G. Remove nut, washer and end caps (32) from upper torsion link pin.
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