>
> I got the torque values from AC 43.13 also. Most of the load is in shear so I don't see any need to go over 85 in/lbs., although the nuts supplied are AN365. The higher torque is proper and certainly won't hurt anything.
>
> -- Guy
Ah, ok thanks Guy. Yeah I checked to be sure today when I got out the wrench, the nuts are the full height AN365 so just used that range on the chart. But you're right it's a primarily shear loading joint. But I'll just keep them at 140 in/lbs on the wrench.
Oh well, since they hold the wing on it was good for me to research all this I guess ;)
Thanks all,
LS
>
>
> ________________________________
> From: ls78705 <lstavenhagen@...>
> To: Titanaircraft@yahoogroups.com
> Sent: Sun, November 29, 2009 9:00:15 PM
> Subject: [Titanaircraft] Re: rear wing hold-down bolts
>
>
>
>
> --- In Titanaircraft@ yahoogroups. com, guy truex <airbosss@ .> wrote:
> >
> > Jeeez... That was supposed to be in/lbs, not ft/lbs.
> >
> > Okay- I'll try it again- aft wing fitting bolts should be tightened to 60 to 85 in/lbs.
> >
> > Sorry about that.
> >
> > -- Guy
>
> Ok, thanks. I actually went ahead and looked up a range of torques in AC43.13, the bolts are AN5 and the locknuts on them are AN365 tension nuts. The range I found on the chart is 100 - 140 in/lbs plus the drag of the nyloc itself. So I torqued them down to 140 on my wrench which would put the torque around the middle of that range figuring about 15 in/lbs or so of drag due to the nyloc insert.
>
> I see 60 - 85 in/lbs listed for the AN364 shear nut, tho... But I have the AN365 nuts.
>
> Hope I didn't torque them down too hard?
>
> Thanks,
> LS
> >
> >
> > ____________ _________ _________ __
> > From: Kimberly Panos <kimberly@ .>
> > To: Titanaircraft@ yahoogroups. com
> > Sent: Sun, November 29, 2009 1:16:55 PM
> > Subject: Re: [Titanaircraft] Re: rear wing hold-down bolts
> >
> >
> > Guy,
> >
> > I was also thinking that 60-85 ft. lbs seems like a lot of torque for an AN-6 bolt. Wouldn't an AN-6 bolt yield, break, or pull the threads off the nut at that torque?. From my engine building days, I recall stock small-block Chevy 3/8" hardened connecting rod bolts were torqued to 45 ft.lbs, and high-performance, high-tensile strength connecting rod bolts in after-market rods may be torqued as high as 55-60 ft lbs. Our AN-6 prop bolts are torqued to just 30 ft. lbs. Anyway, just a thought or brain exercise (I need a lot of that). :-)
> >
> > --Kimberly
> >
> > ----- Original Message -----
> > From: Guy
> > To: Titanaircraft@ yahoogroups. com
> > Sent: Sunday, November 29, 2009 1:59 AM
> > Subject: [Titanaircraft] Re: rear wing hold-down bolts
> >
> > The aft wing fitting attachment bolts need to be tight. If you want to torque them, 60 to 85 ft/lbs. is plenty.
> >
> > The main wing bolts (the front bolts) hold wing fittings in a clevis on the fuselage. Those bolts are in double shear. The nuts only have to hold the bolts in place. There are no flight loads on the nuts. Snug them up until they stop.
> >
> > -- Guy
> >
> > --- In Titanaircraft@ yahoogroups. com, "ls78705" <lstavenhagen@ ...> wrote:
> > >
> > > Hi all,
> > >
> > > JD or anyone, here's a dumb question for you. Is there a particular torque you need to tighten the wing attach bolts to? I was doing a routine inspection of the wing attach areas yesterday and noticed the rear nuts were a little loose.
> > >
> > > However, I can quite see how the attachment is done and I'm reticent to crank the nuts down too tight, for fear of bending/squishin something. It looks like the mounting plate things riveted and glued to the rear of the wing fit flat against the tabs on the cage in the back, and so could (should?) be tightened pretty snug like the front ones are.
> > >
> > > Help me, Obiwan....
> > >
> > > LS
> > >
> >
> > [Non-text portions of this message have been removed]
> >
> >
> >
> >
> > [Non-text portions of this message have been removed]
> >
>
>
>
>
> [Non-text portions of this message have been removed]
>
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