Piper Aircraft Corporation Cherokee 140 PA-28-140, Service Manual

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PIPER CHEROKEE SERVICE MANUAL
01/31/08 III - INSPECTION
3K15
(23) UPPER NOSE GEAR OLEO BEARING INSPECTION. (Refer to Figure 3-24.)
NOTE: Installation of the service replacement upper nose gear oleo bearing P/N 452-419
relieves this 500 hour inspection requirement.
In PA-28-150, -160, -180 S/N’s 28-1 thru 28-90, 28-92 thru 28-365, 28-367 thru 28-764, 28-
766 thru 28-886, 28-888 thru 28-1109, 28-1111 thru 28-1146, 28-1148 thru 28-1154, 28-1156
thru 28-1206, 28-1209 thru 28-1218, 28-1220 thru 28-1223, 28-1225 thru 28-1227, 28-1229,
28-1232, 28-1233, 28-1235 thru 28-1237, 28-1239 thru 28-1245, 28-1248 thru 28-1251, 28-
1253, 28-1255 thru 28-1261, 28-1263 thru 28-1268, 28-1270, 28-1273, 28-1274, 28-1276 thru
28-1280, 28-1286, 28-1287, 28-1293, 28-1285, 28-1301 and 28-1303;
for airplanes which
have not installed upper nose gear oleo bearing (P/N 452-419), each 500 hours, inspect as
follows:
(a) Remove the nose gear steering arm, P/N 63300-08, then remove the threaded collar, P/N
13071-00 and seal washer, P/N 85012-72.
(b) Check that the bearing is in satisfactory condition and installed with loading grooves
facing upward.
(c) Lubricate bearing with MIL-PRF-23827 and reassemble steering mechanism.
(d) If loading grooves are not visible, is will be necessary to lower oleo assembly to remove
bearing. The bearing should be removed, checked, lubricated and installed with the
bearing loading grooves facing upward.
(e) If the bearing is not in satisfactory condition, replace with sealed bearing P/N 452-419.
(24) RUDDER BAR ASSEMBLY 100 HOUR INSPECTION. (Refer to Figure 3-25.)
In PA-28-140 S/N’s 28-20001 thru 28-7325073, PA-28-150, -160, -180 S/N’s 28-03, 28-1 thru
28-7305081, PA-28-235 S/N’s 28-10001 thru 28-7310048, PA-28R-180 S/N’s 28R-30002 thru
28R-7130013 and PA-28R-200 S/N’s 28R-35001 thru 28R-7335089;
for airplanes which have
not modified the original equipment rudder bar assembly, each 100 hours inspect the rudder
bar assembly for cracks. Use light and mirror.
NOTE: The fabricated reinforcement doublers shown in Figure 3-25 , can be installed simply
to relieve this repetitive inspection requirement, even though no cracks have been
detected. Keep in mind, however, that a general visual inspection of the rudder bar
assembly for condition and operation is a normal 100 hour inspection requirement.
(a) If cracks are detected, remove rudder bar assembly from the airplane and repair as shown
in Figure 3-25.
(1) Reinstall rudder bar assembly.
(2) Make proper log book entry.
(b) If no cracks are detected, make proper log book entry documenting completion of this
inspection.