INSPECT THREADS FOR CONDITION (REFER TO OHM 32-16-31 FOR MAXIMUM REPAIR LIMITS) BETWEEN INNER BALL AND OUTER RACE THREADED BEARING ASSEMBLY WITH COTTER PIN THREADED BEARING ASSEMBLY WITH RIVETS SHRINK FIT BEARING ASSEMBLY 737-300/-500 AIRPLANES
737-400 AIRPLANES THE COMBINED WEAR LIMITS OF THE BEARING SUPPORT AND HOUSING CANNOT EXCEED THIS LIMIT
Main Landing Gear Forward Trunnion Bearing Assembly Wear Limits
Figure 601 (Sheet 2)
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E82316
A
737-300/400/500MAINTENANCE MANUAL
(b)
Lift the inner cylinder with the axle jack until you compress the shock strut approximately 1 inch.
(c)
Install a wood 2 x 4 (inches) between the wheel and the shock strut in a horizontal position.
(d)
Twist the gear to fill up all the clearance in one direction.
(e)
Set the dial indicator with the trunnion as near as possible to the forward trunnion bearing.
(f)
Set the dial indicator to zero.
(g)
Use the wood 2 x 4 (inches) to move the gear torsionally.
(h)
Read the bearing clearance on the dial indicator.
(i)
If the clearance is larger than 0.030 inch for shrink fit bearing assemblies, or 0.050 inch for threaded bearing assemblies, examine the worn part limits (see Fig. 601).
(j)
Replace the parts if it is necessary.
E.
Put the Airplane into Its Usual Condition.
S 026-006
(1)
Remove the dial indicator setup.
(a)
Remove the wood 2 x 4 (inches).
(b)
Remove the axle jack.
S 846-007
(2)
Lower the airplane and remove the jacks.
S 606-008
(3)
Clean and lubricate the shock strut (Refer to Chapter 12, Main Landing Gear Shock Strut Servicing).
TASK 32-11-83-206-009
2. Main Gear Forward Trunnion Bearing Assembly Wear Limits (Fig. 601)_______________________________________________________
A. General
(1)
The subsequent data has an illustration and a limit chart for the worn parts. There is no procedure to tell you how to get access to, or remove and install the component after the worn part inspection. Refer to the component removal/installation for the data.
B.
Procedure
(1)
Main Gear Forward Trunnion Bearing Assembly Wear Limits
S 206-010
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737-300/400/500MAINTENANCE MANUAL
MAIN LANDING GEAR AXLE THREAD AND AXLE NUT - INSPECTION/CHECK
______________________________________________________________
1. General
________
A. This procedure only has illustration and a wear limits table which shows the data for wear limits. No procedure is given that permits access for inspection of the parts. Refer to the Main Landing Gear Wheel and Tire -Removal/Installation for procedures to do these tasks.
TASK 32-11-85-206-001
2. Main Landing Gear Axle Thread and Axle Nut Inspection/Check
____________________________________________________________
A. Special Tools and Equipment
(1)
Axle Thread NO-GO Gage Tool for pitch diameter.
(a)
Precise Tool NG2.8750-16 PTG THREADSNAP, used to examine the pitch diameter of the axle thread with undersized configuration.
(b)
Precise Tool NG2.9375-16 PTG THREADSNAP, used to examine the pitch diameter of the axle thread with original configuration.
