29-12: Initial Riveting of the Side Skins

The plans have you backrivet (on the bench) a few components to the side skins, before the skins are clecod to the fuselage sides for riveting. I decided that there were a few additional parts which could be backriveted to the skins, in addition to those called out on page 29-12. To make sure i wasn't missing anything, i clecod these in place and test fit the skin to make sure i wasn't about to do anything stupid! 

This is all the fuselage side skin components which will eventually be installed.

I separated them into left and right side piles.

The centre section side plate and upper drag fitting were back riveted to the skins.

I used my mini-backrivet set - which just fit against the side walls of the upper drag fitting.

Forward Stiffner is riveted only at the front

It's lovely when an area of such big rivets all get set and end up so flat.

Rear ribs are riveted only at the front to give flexibility for installing the aft fuselage in the next chapter

The canopy handle brackets and F01428 side frame were clecod in place

The forward stiffners were also clecod in place

The lower longeron was just balanced into position as you can't cleco this to the skin and then install the skin.

I also clecod on the arm rest - however decided this should be installed AFTER the skins are on the fuselage (see below).

Here i am explaining the order of operations for installing parts on the skins before placing the skins on the fuselage:

The only change to the above plan, was to leave the arm rests until after the skins were installed on the fuselage. This was because these ribs needed some heavy fluting (the skin in this location is very curved), and i was unable to do this fluting on the bench (with the skins flat). 

The arm rest ribs need to be left until the skin is on the fuselage. 

The last riveting on the skins was to install a single nutplate in each skin (it is a grounding point). I am unsure if i will need this (i don't think so) but it doesn't hurt to attach it at this stage. 

This bucking bar was made by my dad and has a hole which takes a standard squeezer die.

I then backriveted the nutplates to the skin.

Canopy Handle Brackets

Before committing to the above plan, i decided to test fit the canopy handle and found that the brackets were a little too close together, leaving the handle very stiff to operate. To fix this, i drilled out the lower bracket, installed the handle with all it's hardware, then riveted the lower bracket to the skin with the handle installed. This made sure the handle would operate freely. I guess, being dimpled components there is a little play in the holes, meaning the brackets went on slightly too close to each other for the handle to fit. 

The lower bracket was riveted with the canopy handle in place.

There is one rivet which is set in-between the 2 brackets which will interfere with the handle when the latch is closed. A small relief hole has to be drilled into the handle to provide space for this rivet. I should have marked this hole onto the handle before dimpling it however i did not! So to get the location for this, i put some torque seal onto the rivet, installed the handle and this transferred the location of the rivet to the handle. I then drilled a shallow depression for the rivet to nest into when the handle is closed.

As you can see i installed rivets into the 2 holes left over from the old rivet line (for the stock canopy latch handle brackets). 

Clecoing the skins to the fuselage

The skins were then slid into position on the fuselage and clecod in place. The upper drag fitting bolt was reinstalled (with TefGel) and I torqued the nut - i found the running drag on these nuts to be 15in/lbs. Looking up the torque table in Section 5 for an AN6 bolt i found the torque was 160-190 in/lbs. Taking the middle value (175 in/lbs) plus the running torque i did these up to 190in/lbs. 

Can anyone see the problem here??? 

As i was writing this blog, i realised these bolts and nuts are AN5 bolts and AN365-524 nuts. NOT AN6 (the lower drag fittings are AN6). Looks like i will be undoing these nuts when i get home from work today and redoing them to 140 in/lbs. Oops. The value of review in this blog has just been demonstrated! 

Getting out the black goo once again!

When clecoing on the skins, the plans call for the use of some fuel tank sealant to seal the seam between the firewall and the side skins, however it also calls for some fuel tank sealant along the forward section of the side skin where it lays down on the upper longeron. The sealant at the firewall is to prevent noxious gasses etc entering the cockpit in the event of a firewall forward fire, so for this i will use the 3M FireBarrier 2000+, as i have done previously. However, the tank sealant laid down horizontally along the skin edges (along the upper longeron) i can only assume is there to prevent water ingress. Since the 3M sealant is a silicone based product, and the side skin will need to be painted, i decided to use fuel tank sealant for the horizontal skin seal against the upper longeron. 

Which meant it was time to break out the black goo again! (i actually had to buy another can - this stuff is expensive - hopefully this is my last can). 

I held the skin away from the fuse using wooden blocks.

And masked up the areas where didn't want the proseal to end up

I then applied the 3M Firebarrier 2000+ to the firewall flanges, making sure to seal all gaps between the rib notches in the firewall sheet. 

I cleco'd every hole and will let the sealant set up for a day before riveting this section.

I made sure to seal off all areas where water ingress could occur.

I also sealed off all areas where noxious gasses could pass from the engine compartment to the cabin.

Next up will be to actually start setting some rivets in the side skins!