Piper PA-28-161, Maintenance Manual

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PIPER AIRCRAFT, INC.
PA-28-161, WARRIOR III
MAINTENANCE MANUAL
PAGE 3
Nov 30/06 4G23
57-10-00
(3) Inspection
CAUTION: USE EXTREME CARE IN REMOVING AND REPLACING THE WING MAIN
SPAR TO FUSELAGE (I.E. - SPAR CARRYTHROUGH) ATTACHMENT BOLTS
(18 PER SIDE) TO PRECLUDE DAMAGING THE BOLT HOLES OR BOLT
HOLES. DO NOT DRIVE THE BOLTS IN OR OUT OF THE HOLES. AS THE
BOLTS ARE REMOVED, NUMBER EACH BOLT AND HOLE TO ENSURE
REPLACEMENT IN THE SAME HOLE. USE PROPER TORQUE VALUES WHEN
INSTALLING BOLTS. IF REPLACEMENT OF SOME BOLTS IS REQUIRED,
ENSURE PROPER PART NUMBER AND GRIP LENGTH. INSTALLATION OF
EIGHTEEN (18) NEW NUTS (SEE BOLT LEGEND, FIGURE 1, 57-40-00)
DURING WING REINSTALLATION IS RECOMMENDED.
(a) Remove both wings in accordance with Wing - Removal, 57-40-00.
(b) Visually inspect, using a 10-power (minimum) magnifying glass and a dye-penetrant
method or equivalent, for cracks in the wing lower spar cap from the wing skin line
outboard of the outboard row of wing attach bolt holes to an area midway between the
second and third row of bolt holes from the outboard row.
1 If no cracks are found, prior to further flight, accomplish the actions specified in
paragraph (c) below.
2 If any cracks are found, prior to further flight, replace the spar or wing with a new or
serviceable unit shown to be free of cracks when subjected to the inspections
specified in this paragraph.
(c) Visually inspect for cracks in each upper wing skin adjacent to the fuselage and forward of
each main spar.
1 If no cracks are found, reinstall the wings in accordance with Wing - Installation,
57-40-00.
2 If cracks are found, prior to further flight, replace with new parts or repair in
accordance with latest revision of AC 43.13-1, and reinstall the wings in accordance
with Wing - Installation, 57-40-00.
(d) Make an appropriate entry in the aircraft logbook documenting this inspection and any
maintenance actions taken as a result.
2. W.S. 36.22 Right Side Wing Rib 100 Hour Inspection
In S/N’s 2842001 through 2842178, for airplanes which have not installed Piper Kit No. 767-363, each
100 hours, inspect the rib at W.S. 36.22 in the right wing for cracks.
NOTE: Installation of Piper Kit No. 767-363 relieves this repetitive inspection requirement.
A. Open the panel on the lower right hand wing just outboard of wing station 36.22, Figure 1. Visually
inspect the P/N 62066-000 rib for crack development in the area shown in Figure 1.
B. If no evidence of cracking is found, close the access panel.
C. If cracking is found, repair per Piper Kit P/N 767-363.