737 AMM 飞机维护手册 起落架 LANDING GEAR(42)

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NOTE:  Support bracket (24) is connected to torsion link with flat head pins secured by washer and cotter pin.
CAUTION: DO NOT USE BOLTS. BRACKET MUST PIVOT FREELY ON TORSION LINK.
AA. Place hydraulic lines in position on each side of main gear damper. Connect hydraulic line guides (16) to damper. Tighten bolts to standard torque.
AB. On right gear, connect spoiler lockout teleflex cable to upper torsion link.
AC. Lubricate torsion links (Ref Chapter 12, Landing Gear Component Lubrication).
AD. Install main gear brakes if removed (Ref 32-41-41, Removal/Installation) and main gear wheels (Ref 32-45-11, Removal/Installation).
AE. Pressurize hydraulic system and remove and install damper bleed plugs one at a time. Finally open filler valve. In each case, allow fluid to flow until clear of air before replacing plugs and closing valve.
AF. Check damper hydraulic return line connection for leaks.
AG. Lower airplane if airplane was raised and remove jacks (Ref Chapter 7, Jacking Airplane).
501 
Feb 1/74  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-11-51 Page 405 

MAIN GEAR TORSION LINKS - INSPECTION/CHECK
1.  General
A.  These data consist of illustrations and wear limit charts. No procedure is given in this section for access to permit inspection. Refer to Main Gear Torsion Links - R/I for removal procedure.
2. Main Gear Torsion Links Wear Limits

501  Main Gear Torsion Links Wear Limits 
Aug 01/94  Figure 601 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-11-51 Page 601 

G43343
Main Gear Torsion Links Wear Limits  5A5 
32-11-51 Page 602  Figure 601 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/01 

 

501  Main Gear Torsion Links Wear Limits 
Aug 01/94  Figure 601 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-11-51 Page 603 

Main Gear Torsion Links Wear Limits  501 
32-11-51 Page 604  Figure 601 (Sheet 4) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 01/95 

MAIN LANDING GEAR TORSION LINKS - APPROVED REPAIRS
1.  General
A.  This procedure contains a task that will let you correct the axial clearance that is too large. You can correct the axial clearance with shims at specified landing gear components' locations.
B.  This procedure is for temporary repairs only. The recommended overhaul rework is to put the part back to the initial limits with the new bushings.
2.  Main Landing Gear Torsion Link Axial Clearance Correction (Fig. 801)
A.  References
(1)  
32-11-51/401, Torsion links - Removal/Installation

(2)  
32-11-51/601, Torsion Links - Inspection/Check

B.  Procedure
(1)  
Remove the torsion link (Ref 32-11-51/401).

(2)  
Do a check of the parts (Ref 32-11-51/601).

(3)  
Make the shims if it is necessary, refer to Fig. 801.

(4)  
Install the torsion link with the shims between the bushing flanges, refer to Fig. 801 (Ref 32-11-51/401).

500 
Oct 20/93  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-11-51 Page 801 

 

Special Repairs - Shim Axial Clearance  500 
32-11-51  Figure 801 (Sheet 1)  Oct 20/93 
Page 802 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

 

B48272
500  Special Repairs - Shim Axial Clearance 
Oct 20/93  Figure 801 (Sheet 2)  32-11-51 
Page 803 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

MAIN GEAR SIDE STRUT - REMOVAL/INSTALLATION
1.  Equipment and Materials
A.  Gear Ground Assemblies (Ref 32-00-01)
B.  Airplane jacks
C.  Grease - MIL-G-21164 or MIL-G-23827 optional to BMS 3-33
2.  Prepare to Remove Main Gear Side Strut
A.  Check that all gear ground lock assemblies (Ref 32-00-01) are installed.
B.  Depressurize hydraulic system.
C.  Jack airplane to take weight off gear (Ref Chapter 7).
3.  Remove Main Gear Side Strut
A.  Disconnect main gear downlock sensor (5, Fig. 401). Release all cable connections from side strut, slip cable through slot in sensor bracket, coil cables and tape switch clear of side strut (Ref 32-61-31)/
B.  Support the inboard wing door and the side strut. Disconnect the upper side strut, slip cable through slot in sensor bracket, coil cables and tape switch clear of side strut (Ref 32-61-31).
　
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