Return-Path: Sender: (Marvin Kaye) To: lml Date: Wed, 22 Jan 2003 15:38:54 -0500 Message-ID: X-Original-Return-Path: Received: from swan.mail.pas.earthlink.net ([207.217.120.123] verified) by logan.com (CommuniGate Pro SMTP 4.0.5) with ESMTP id 1995159 for lml@lancaironline.net; Wed, 22 Jan 2003 15:37:02 -0500 Received: from sdn-ap-007watacop0038.dialsprint.net ([65.176.64.38] helo=f3g6s4) by swan.mail.pas.earthlink.net with smtp (Exim 3.33 #1) id 18bRcK-0000jx-00 for lml@lancaironline.net; Wed, 22 Jan 2003 12:37:01 -0800 X-Original-Message-ID: <008201c2c256$58622c00$2640b041@f3g6s4> Reply-To: "Dan Schaefer" From: "Dan Schaefer" X-Original-To: "Lancair list" Subject: LNC2 Nose gear pivot tab hole elongation X-Original-Date: Wed, 22 Jan 2003 12:39:20 -0800 MIME-Version: 1.0 Content-Type: text/plain; charset="Windows-1252" Content-Transfer-Encoding: 7bit X-Priority: 3 X-MSMail-Priority: Normal X-Mailer: Microsoft Outlook Express 6.00.2800.1106 X-MimeOLE: Produced By Microsoft MimeOLE V6.00.2800.1106 Scott, et al. The part you're talking about is similar in function to the anchored end of the over-center links on the main gear (the one that has the rod end bearing and attaches to the bolt-up on the gear leg). Back in '93, just days before first flight on my LNC2, a hangar mate had one of his fail on take-off and his airplane was messed up pretty bad. The failure mode was due to poor design (sorry Lance!) where a AN490 Threaded Rod End (male) had it's plain end inserted into a matching hole bored in end of the o/c aluminum link and affixed with structural adhesive and a 3/16 thru-bolt. (This deficiency has since been addressed by the factory). At the time (and looking at the resulting damage to the "incident" Lancair) I redesigned the part to eliminate the failure mode and had a local machinist make some up for me. I took him the original part, he basically copied it for dimensions and then included my changes. He charged about $95 per pair when I had a dozen sets made. The redesign changed the material to steel - the machinist suggested a high strength alloy that was also tough - and used a threaded hole (NF - Class 2, if I remember) in which a length of stainless All-thread was inserted extending to the same length as the AN490. The rod-end was then installed on the All-thread shaft to the same dimensions as the AN490 and reinstalled on the airplane. The reason for relating this saga is to suggest that the same thing could easily be done to the nose gear o/c link part to get the rod-end bearing where you suggest to eliminate the wear point. It's unlikely that a rod-end ball will be exactly a snug fit between the tabs but some judicious shimming with washers would probably do the trick, allowing the ball to be firmly captured by a bolt. Cheers, Dan Schaefer