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

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PIPER CHEROKEE SERVICE MANUAL
01/31/08 III - INSPECTION
3J11
(8) WING RIB ASSEMBLY W.S. 49.25 INSPECTIONS.
The left and right rib assemblies in PA-28R-180/200’s , aft of the main spar at W.S. 49.25 can,
under certain conditions, crack. The cracking is typically observed vertically along the bend
radius of the flange common to the main spar and the main landing gear side brace attach
fitting (see Figure 3-6). Accordingly,
in PA-28R-180/200’s only , perform the following
inspections at the intervals indicated:
NOTE: Installation of Piper Kit(s) No. 767-397 (LH) and/or 767-398 (RH), eliminates the
following 100 hour and 500 hour repetitive inspection requirements for the side(s)
affected.
NOTE: In the rare instance that service replacement wing rib assembly(s) (P/N 78475-004
and/or 78475-005) with date codes of 8313 (see Figure 3-7) or higher (i.e. -
manufactured circa July 2005 or later) have been installed at W.S. 49.25
these
inspections are not required for the side(s) affected.
(a) 100 Hour Wing Rib Inspection.
Except as described above, each 100 hours time-in-service:
1 Place the airplane on jacks per Sec. II, Para. 2-13.
2 In both the right and left wings:
a
Inspect the Aft Rib Assembly at W.S. 49.25 for any evidence of cracks (see
Figure 3-6.)
b Inspection shall be limited to a visual examination.
c Inspect the exposed (upper half) portion of the bend radius of the flange
common to the Aft Rib Assembly and the Main Spar Web.
3 If any crack is detected visually, proceed to a more detailed examination.
a
Remove the Main Landing Gear Side Brace, by removing the five (5) bolts that
fasten it to the wing structure. Retain hardware for reassembly.
b Inspect the cracked Rib Assembly in the bend radius of the flange common to
the Main Spar Web, using dye penetrant inspection techniques, to determine the
full extent of crack propagation.
c Determine if trimming, as shown in Figure 3-6, will remove all the material
affected by the crack.
1)
If so, install the appropriate kit (see above).
2) If this cannot be accomplished, replace the cracked Rib Assembly.
4 If no cracks are detected, reassemble/reinstall any parts or components previously
removed.
5 Verify proper functioning of landing gear.
6 Verify gear are down and locked and remove airplane from jacks.
7 Make an appropriate logbook entry.