(8)
Check hydraulic damper on torsion links for security and leaks.
(9)
Examine side strut and drag strut connections to side strut universal connection for tightness, corrosion and missing cotter pins.
(10)
Check attachment lugs of torsion links, side strut, and drag strut for cracks.
(11)
Check upper drag strut attachment for security and improper locking.
(12)
Check trunnion link and hydraulic swivel for security and damage. Check swivel for leaks.
(13)
Check reaction link attachments, lock actuators, and uplock hook for security and damage.
(14)
Check downlock strut for loose attachments and damage.
(15)
Check for end play in actuator and walking beam attachment bolts.
(16)
Check wing door attachments at shock strut and side strut for looseness and improper locking.
(17)
With shock strut jacked, gage axle nut threads with machinists ID micrometer or with axle nut thread gage to check that thread minor diameter does not exceed 2.8785 inches. If axle nut thread gage can be passed through axle nut, nut should be replaced.
500
Nov 15/78 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-11-0 Page 601
C. Main Landing Gear Torsional Free Play Inspection
(1)
General
(a) The torsional play of each main gear must be within tolerance to ensure satisfactory shimmy stability.
(2)
Equipment and Materials
(a)
Dial indicator gage -0 to 0.5 inch
(b)
C-clamp - 12-inch
(c)
Wooden 2 X 4 -approximately 10 feet long
(d)
Sturdy box or platform - approximately 15 inches high with suitable mounting for dial indicator gage
(e)
Spring scale
(3)
Prepare for Examination
(a)
Jack airplane until main gear is clear of ground. Refer to jacking airplane in Maintenance Manual, Chapter 7.
(b)
Deflate shock strut by slowly opening air valve at top of strut. Care should be taken to ensure no loss of fluid through air valve.
WARNING: DO NOT LOOSEN VALVE BODY UNLESS SHOCK STRUT IS COMPLETELY DEFLATED. AIR PRESSURE CAN BLOW VALVE BODY OUT, CAUSING INJURY TO PERSONNEL.
(c)
With 12-inch C-clamp, clamp shimmy damper in fully closed position to eliminate damper motion (Fig. 1).
(d)
Set up dial indicator gage on box to read fore and aft motion of inboard wheel rim. Gage should be located on forward side of wheel on horizontal plane of axle centerline (Fig. 1).
(e)
Insert 2 X 4 between shock strut and outboard wheel (Fig. 1).
(4)
Measure Torsional Free Play
500
32-11-0 Page 602 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Sep 01/02
NOTE: The shimmy damper must be adjusted correctly and the apex nut of the torsion link is tightened to the specified torque before you do a check on the torsional free play of the main landing gear (Ref 32-11-81 A/T).
(a)
With aid of a spring scale, apply a clockwise pull of 30 pounds on 2 X 4 at 100-inch arm from shock strut centerline. Set the dial indicator gage to zero and relax load.
(b)
Apply a counterclockwise pull on 2 X 4 as in step (a). Record dial indicator reading and relax load.
(c)
Repeat steps (a) and (b) for a total of 5 cycles.
(d)
Deleted.
(e)
Determine average free play for 5 cycles.
(f)
Average value determined in step (e) should be less than 0.147 inch when standard tires, 40 X 14-16, are installed, and 0.140 inch when H40 X 14.5-19 tires are installed.
(g)
If average value is greater than maximum allowable, the following parts or assemblies should be checked for permissible wear and appropriate parts replaced: 1) Torsion links 2) Shock strut inner and outer cylinder torsion link attachment lugs 3) Trunnion link to outer cylinder clevis joint 4) Forward trunnion bearing 5) Aft trunnion bearing
(h)
If parts are replaced, repeat steps (a) thru (g) to verify that torsional free play is within limits.
Aug 01/96 32-11-0
Page 603
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(5) Restore Airplane to Normal
(a)
Remove 12-inch C-clamp from shimmy damper.
(b)
Service shock strut with air to 250-psi extend pressure prior to lowering airplane.
(c)
Lower airplane and remove jacks.
Main Landing Gear Torsional Free Play Inspection 500
32-11-0 Figure 601 Feb 01/95
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