(8)
Check steering collar bearing for dirt and wear.
(9)
Check wheels for cracks, corrosion, and flaked paint.
(10)
Check drag brace links for cracks and wear at attach points.
(11)
Check drag link and shock strut trunnion pins for wear and looseness.
(12)
Check nose gear and nose gear lock actuators for loose mounting bolts and evidence of fluid leakage.
(13)
Check lock link spring assembly attach points for wear and looseness.
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C. Nose Landing Gear Torsion Free Play Inspection
(1)
Equipment and Materials
(a)
Dial indicator gage - 0- to 0.25-inch minimum
(b)
Wooden 2 x 6 - Approximately 7 feet long
(c)
Sturdy box or platform - Approximately 15 inches high with suitable mounting for dial indicator gage
(d)
Spring scale - 0- to 50-pound capacity
(e)
Nose Gear Steering Actuator Rod Clamp - F80162-1
(f)
Axle jack
(2)
Prepare for Examination
(a)
Check that hydraulic systems A and B are depressurized (Ref 29-11-0 and 29-12-0).
(b)
Jack nose of airplane until nose gear shock strut is fully extended (Ref Chapter 7, Jacking).
(c)
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.
(d)
Use axle jack to jack nose gear inner cylinder until approximately 4 inches of chrome surface is visible on inner cylinder.
(e)
Install nose gear steering actuator rod clamps on both steering actuator rods. Position clamps tightly against actuator end plates to prevent any movement of actuator rod.
(f)
Set up dial indicator gage on platform to read fore and aft motion of right wheel rim. Gage should be located on forward side of wheel on axle centerline (Fig. 601).
(g)
Insert wooden 2 x 6 between wheels.
(3)
Measure Torsional Free Play
(a)
With the aid of a spring scale, apply a clockwise pull of 30 pounds on wooden 2 x 6 at a 60-inch arm measured from shock strut centerline. Set the dial indicator gage to zero and relax load.
(b)
Apply a counterclockwise pull on wooden 2 x 6 as in step (3)(a). Record reading on dial indicator and relax load.
(c)
Repeat steps (3)(a) and (3)(b) for a total of five cycles.
(d)
Deleted.
(e)
Determine average free play for five cycles.
(f)
Average value determined in step (3)(e) should be less than 0.092 inch.
NOTE: 0.092-inch free play corresponds to 0.0082 radian.
(g)
If the average value is greater than the maximum allowable, repeat step 3(a).
(h)
Use feeler gages to measure the gaps between the bushing flanges at the upper, lower and apex joints of the torsion links.
(i)
If the free play exceeds 0.004 inch, assemble stainless steel shim washers to put back the gaps to 0.001 inch.
NOTE: The shim washer profile should match the profile of the mating bushing flange.
(j)
If the diameters of the pin or bushing bore are more than their wear limits, replace these parts.
(k)
After the installation of the torsion link pins, do another check for the torsional free play.
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Aug 01/94 32-21-0
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(l)
If the torsional free play is satisfactory, return the airplane to normal.
(m)
If the torsional free play is still more than the maximum allowance, remove the nose gear steering collar (Ref 32-51-61, 401).
(n)
Do a check on all the interface dimensions that are common to the steering collar, steering collar bearing, and the bushing and bolts of the rod end attachment of the steering cylinder.
(o)
Replace any of the parts, which show signs of wear.
(p)
After installation of the steering collar components, do another check for torsional free play.
(q)
If the check is satisfactory, return the airplane to normal.
(r)
If the torsional free play still exceeds the maximum allowance, remove the nose gear shock strut assembly (Ref 32-21-0, 401).
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