A mechanic writes, “On a routine 100 hour inspection a crack was found on the horizontal stabilizer’s front apex: (specifically) the lower angle (P/N 0432001-44: see photo number 1) and the reinforcement plate (P/N 0432001-44: photo number 2). The lower skin rivet seam (was also found) fretted and loose (photos 3 and 3A.) Upon removal and disassembly (additional defects) ...were discovered: cracked skin (P/N 0432001-55: photo 4) and a cracked spar (P/N 0432001-56: photos 5 and 6).

“This is an earlier serial numbered aircraft which apparently did not have the reinforcement angle (P/N 0432007-3) as installed on later serial numbered aircraft. This aircraft also has Bolen’s ‘conversion to tail wheel’—it has spent a portion of its total time (in this configuration).” The Supplemental Type Certificate number provided for this conversion is SA 175GL. (Excellent sequential documentation: thank-you! Of the seven photos, I could rationalize cutting only the close-up number six—but I didn’t. Each tells a piece of this story: the close-up should drive it home. All of these pictures have been cropped and vertically compressed. Some day...soon...we hope to facilitate appending documents and photos to the electronic, defect submission forms—or
maybe a separate server/mail account, etc. Currently I have to scan—what you already have scanned—which doesn’t help the “picture,” right?—Ed.).

Part Total Time: 8,207.6 hours.