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  #1  
Old 11-09-2018, 12:31 PM
Zazoos Zazoos is offline
 
Join Date: Oct 2017
Location: Gladewater
Posts: 141
Default Wing Attach 5/8 Distance

Working on the right wing. Per the plumb bob it is swept forward 1 inch.

The wing rear spar is fully seated and touching the fuselage. The fuselage rear spar forward piece of the fork is touching the wing rib.

I marked my 5/8 distance grid on both pieces. The inside 5/8 distance on the fuselage is measured from where the two forks mate an become a solid spar.
The inside 5/8 on the wing rear spar is measured from the root rib flange.

Questions:
1. Since the both spars obviously continue in there respective directions can the inside 5/8 distance be somewhat ignored? Otherwise as you can see in my grid layout I really do not have the room to remove any materials (especially on the wing rear spar).
2. If I'm correct that the inside edge distance can be ignored, is there a good ratio as to how much material to remove to get close to a 1 inch movement at the wing tip?





Thank you,
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  #2  
Old 11-09-2018, 12:55 PM
bscycleman bscycleman is offline
 
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Location: San Antonio, TX
Posts: 58
Default Also applies to the wing spar

The short answer is the inside clearance matters as well. The rear wing spar sits between the plates and drives the inside edge distance needed.

Brian
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  #3  
Old 11-09-2018, 01:36 PM
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az_gila az_gila is offline
 
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Location: 57AZ - NW Tucson area
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Smile

Some of us had to trim the top web of the rear spar a bit to keep it clear of the top of the fuselage slot. This lets the spar slip a bit further into the fuselage.

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  #4  
Old 11-09-2018, 02:08 PM
Zazoos Zazoos is offline
 
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Location: Gladewater
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Default

Quote:
Originally Posted by bscycleman View Post
The short answer is the inside clearance matters as well. The rear wing spar sits between the plates and drives the inside edge distance needed.

Brian
Just to make sure I'm on the same page about what I am calling the inside.





The way I see it the spar material continues either towards the center of the fuselage or towards the wing tip. Hence the edge distance there doesn't seem as important. With that said, I can certainly could have a flawed thought process. That is why I want to be as clear as possible, because I do not want to foul this up.

Thank you again,
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  #5  
Old 11-10-2018, 05:59 AM
doug_rv7 doug_rv7 is offline
 
Join Date: May 2005
Location: Lincoln, NE
Posts: 73
Default 5/8 distance

I'm at this point on my RV-7 as well. Looking at Gil's diagram, it looks like it applies to the outside of the spars coming out of the fuselage. Bottom line, if you have at least 5/8" of real estate all around your hole, I think you're good.

Doug
RV-7
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  #6  
Old 11-10-2018, 03:59 PM
FinnFlyer FinnFlyer is offline
 
Join Date: Aug 2018
Location: Bell, FL
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Default

From http://vansaircraft.com/pdf/Wing_%20Incidence.pdf

(search for "incidence" on Van's web site)

"3: If there is a sweep or triangulation problem STOP. The common reasons are:
A: The rear spar structure that sticks out of the fuselage is comprised of
two pieces of 1/8? aluminum bar. One piece ends up on the front side of the wing rear spar stub and one is on the back side (where you can see it). The forward piece OFTEN is too long and hits the wing root rib flange and prevents sufficient
insertion of the rear spar stub into the ?hand? of the fuselage (thus producing
forward sweep). If so, then remove the wing and cut off the minimum amount
required to correct for the sweep error. In general, if the tip of the wing is swept
forward 1? then trim 1/8? to ?? from the end of the bar.
B: Sometimes the culprit is the wing rear spar stub! If it is running into the
spacer block in the ?hand? of the fuselage, and that is all that is wrong, then
remove the wing and trim off as in ?A? above."

The only issue I can think of is hole-to-hole clearance between the hole you are trying to drill and and hole further inboard. Is there a bolt through the spacer mentioned above in the RV-6?

Finn
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  #7  
Old 11-10-2018, 04:57 PM
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JonJay JonJay is offline
 
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Location: Battleground
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Default

Quote:
Originally Posted by Zazoos View Post
Just to make sure I'm on the same page about what I am calling the inside.





The way I see it the spar material continues either towards the center of the fuselage or towards the wing tip. Hence the edge distance there doesn't seem as important. With that said, I can certainly could have a flawed thought process. That is why I want to be as clear as possible, because I do not want to foul this up.

Thank you again,
I think I understand what you are saying, and yes, if there is no edge you don't have edge distance to be concerned with on the "inside" as you reference. However, you need enough clearance to get a socket/wrench on the bolt and nut clear of the fuselage skin, so be mindful of that.
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  #8  
Old 11-10-2018, 05:28 PM
lr172 lr172 is offline
 
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Location: Schaumburg, IL
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Edge distance is the distance from the holes center to the edge of the material. If there is no edge, as in what you call the "inside," then by definition there is no edge distance to account for. However, in this case, two pieces of material are mating with the edges opposite one another and therefore the holes location is constrained on both sides. Your placed hole must provide the appropriate edge distance for both pieces.

Larry
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Last edited by lr172 : 11-10-2018 at 05:31 PM.
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  #9  
Old 11-10-2018, 07:10 PM
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az_gila az_gila is offline
 
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Location: 57AZ - NW Tucson area
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Default

Quote:
Originally Posted by doug_rv7 View Post
I'm at this point on my RV-7 as well. Looking at Gil's diagram, it looks like it applies to the outside of the spars coming out of the fuselage. Bottom line, if you have at least 5/8" of real estate all around your hole, I think you're good.

Doug
RV-7
Mounting the wings
I'm not sure if my description was clear, so I added red to the OP's picture -



Finn also mentioned this relative to incidence, but it also affects the sweep. -

B: Sometimes the culprit is the wing rear spar stub! If it is running into the
spacer block in the “hand” of the fuselage, and that is all that is wrong, then
remove the wing and trim off as in “A” above."


The spacer block, shown as a rivet hole on sheet 26, but becomes a AN3 bolt on sheet 33, can certainly affect how far the wing rear spar penetrates the fuselage.

The bolt can be removed and the spacer - fabricated from 1/4 inch stock - can be trimmed down a bit on the outer side or flipped for more clearance..
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Grumman Tiger N12GA - flying
La Cholla Airpark (57AZ) Tucson AZ

Last edited by az_gila : 11-10-2018 at 11:29 PM.
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  #10  
Old 11-10-2018, 10:58 PM
arffguy arffguy is offline
 
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Location: Elk Grove, CA
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Default

The notch on the rear spar that Gil refers to is on plan sheet fourteen, revision ten, dated 7/1994.
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