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

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TABLE III-I - INSPECTION REPORT - PA-28-140/150/160/180/235
K. NOTES (CONT.)
PIPER CHEROKEE SERVICE MANUAL
01/31/08 III - INSPECTION
3I1
21. If not accomplished already, create access panels for inspection (refer to Sec. IV, Para. 4-79).
Inspect stabilator control cables.
22. In PA-28-140 S/N’s 28-20001 thru 28-7725290, PA-28-150, -160, -180 S/N’s 28-1 thru 28-
4377, PA-28-235 S/N’s 28-10001 thru 28-11039, for airplanes with the original equipment
“butterfly” control wheels still installed,
perform the 100 Hour Control Wheel Inspection (see
Special Inspections, Procedures).
23. If the landing light is located in the air filter and the improved Landing Light Support P/N
85174-002 has not been installed, perform Landing Light Seal Inspection, (see Special
Inspections, Procedures).
24. In PA-28-140 S/N’s 28-20000 thru 28-26233, PA-28-150, -160, -180 S/N’s 28-1 thru 28-5611,
PA-28-235 S/N’s 28-10001 thru 28-11300,
perform Aileron Hinge Doubler 100 Hour
Inspection (see Special Inspections, Procedures).
25. In PA-28-235 S/N’s 28-10001 thru 28-74100093, for airplanes which have not installed Piper
Kit No. 757-148 (with the 1-H65-2 valve) or 760-895:
each 50 hours, perform the Fuel
Selector Valve 50 Hour Leak Check (see Special Inspections, Procedures).
26. For airplanes which are not equipped with forged main landing gear strut cylinders P/N 65489-
002 on both left and right sides, perform Cast Main Landing Gear Strut Cylinder 100 Hour
Inspection (see Special Inspections, Procedures).
27. During inspection of throttle, determine if there is internal cable ballooning. If so, replace the
affected cables.
28. 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; for airplanes which have not
modified the original equipment rudder bar assembly per Figure 3-25,
perform Rudder Bar
Assembly 100 Hour Inspection (see Special Inspections, Procedures).
29. In PA-28-180 S/N’s 28-5153 thru 28-7405188 and PA-28-235 S/N’s 28-7310001 thru 28-
7410081; for those airplanes which have not installed Piper Kit No. 760-890 (PA-28-180) or
760-891 (PA-28-235):
inspect throttle and mixture cable forward end balljoints for excessive
wear (see Figure 8-10a).
30. Verify torque at forward and aft spar attach per Section IV, Figure 4-2. Retorque wing aft spar
attach bolts per Wing Aft Spar-to-Fuselage Attachment Hardware 100 Hour Inspection (see
Special Inspections, Procedures).
31. Verify initial compliance with Piper Service Bulletin No. 886.
32.
In PA-28-180 S/N’s 28-7105001 thru 28-7505046 and PA-28-235 S/N’s 28-7110001 thru 28-
7510016
: inspect the quick-disconnect mechanism for each rear seat per Rear Seat Quick-
Disconnect Mechanism Inspection (see Special Inspections, Procedures).