Nov 25, 2023     Week 33 - (25 hours)       Category: Fuselage

Work on the battery box continued where we left off last week. Steps 3, 4, 6, and 7 completed final assembly of the box. Step 5 was skipped for now due to a lack of sealant which is on order. The assembly took awhile because some of the rivets were a little difficult to get to. Meanwhile, looking somewhat ahead, the panel attach strips were prepped by dimpling and riveting nutplates to the panel attach strips (step 6 on 29iS/U-11.) The glareshield was prepped for installation by completing steps 1, 2, and 3 on page 29iS/U-10. Boelube was then applied to the glareshield as directed in step 1 of 29iS/U-11. The mating surface was then cleaned and a bead of Permatex silicone adhesive was carefully laid along F-01201H-1 as described in step 3. The glareshield was then installed on the airframe using screws (step 4.) The small plate that sits on top of the glareshield was then screwed into place. The plate had to be trimmed slightly to fit exactly. The panel attach strips were added next as described in step 7. Meanwhile, a small group assembled the egress handle as outlined in steps 4 through 6 on page 29iS/U-10. The handle assembly was then riveted in place in step 8 of 29iS/U-11. The upper panel plate was then attached to the strips using screws (step 9.) Except for some needed fuel sealant in places, that completed the fuselage kit. For the moment, the fuselage is being set aside in a corner of the chapter hangar. We have the wing kit and a lot of priming prep work needs to be done on that before assembly. Meanwhile, our Cessna 150M restoration project needs some attention since the fuselage has returned from the paint shop.

  Nov 18, 2023     Week 32 - (35 hours)       Category: Fuselage

The forward upper fuselage was the focus of this week's sessions. Beginning with step 1 on page 29iS/U-04, we once again dealt with the messy, thoroughly nasty fuel tank sealant to continue the process of sealing off the firewall. Thus sealed, we then installed and riveted the upper firewall assembly to the fuselage (step 2). In steps 3 and 4, the short cowling attach hinge pieces were match drilled and installed. More sealant was then applied under the F-01201B-1 firewall shelf where it meets the skin. Two stiffeners were then added to each side of the forward skin followed by yet more sealant. We then moved on to page 29iS/U-08 (05, 06, and 07 having been completed.) The F-01202B-1 avionics shelf was first test fitted to be sure the edges aligned with the fuselage side skins. Some minor filing was needed to get a perfect match. Once we were satisfied with the fit, holes were match drilled through the shelf into the 1255 longerons. The canopy rib assemblies were then added and also match drilled. In steps 4, 5, and 6 the shelf, canopy ribs, and 12132 brackets were all riveted onto the 1255 longeron structure. The forward edge of the shelf was then riveted to the upper firewall and nut plates installed. The next step on that page is to add more fuel tank sealant. But by this time the 2 hour pot life of our supply of sealant had expired. So that had to be marked as “to do” and we moved on to the battery box on page 29iS/U-09. The parts for the battery box had been prepped and clecoed together earlier. It was first disassembled and the first two steps were completed. That is where we ended this week's sessions. Steps 8 through 11 on that page were completed earlier.

  Nov 04, 2023     Week 30 - (30 hours)       Category: Fuselage

Progress was made on several fronts this week. On the upper forward fuselage work continued on page 29iS/U06. The canopy rib assemblies have proven to be more time consuming and confusing than they look. We've already had to replace a part. The right one is finally complete while the left one is awaiting the replacement part. Read the directions very carefully for these parts! Another team worked on the steps on page 29iS/U07. This section is also quite complicated and requires careful reading. By the end of the sessions all steps were completed. Note: We are putting in a single Garmin EFIS, so the directions were followed for that setup. Meanwhile, the rudder pedals were temporarily installed completing steps 8 and 9 on page 28iS/U-03. They are a little tricky to install because of the arrangement of washers, but everything fit well. We later had to remove the pedals temporarily to work on the forward fuel lines. Bending and shaping fuel lines was another challenge begun this week. We began with the fuel tank to shut-off valve line on page 27iS-04. None of us were very experienced dealing with tubing, so we took it slowly and completed the steps on that page. We then moved on to the tube on page 27iS-05. This one was a little more difficult because once fabricated, it does not easily fit where it belongs. The note, “When installing fuel lines it is acceptable to bend a large radius curve by hand to ease installation, the restraighten afterwards” is important. We recruited one of the chapter members working on the Zenith Veterans Build who showed us how to do this. We were able to fabricate the tube and test fit it by the end of the session. Meanwhile, we had some other volunteers show up, so we gave them the task of beginning to prep wing ribs.

  Oct 28, 2023     Week 29 - (35 hours)       Category: Fuselage

Work this week focused on the upper firewall and brake lines. Continuing on page 29iS/U-03, steps 8 through 15 were completed, finishing the page. The upper firewall assembly was then test fitted to the fuselage. Meanwhile, the rudder pedal assembly had been completed up through step 7 on page 28iS/U03. Step 8 involves mounting the completed assembly into the fuselage. Looking ahead, the steps that follow involve adding the brake lines. We decided it would be easier to install the brake lines first on a table rather than try to reach them inside the fuselage. So we moved on to 28iS/U-04 and installed the cross-over brake lines in steps 1 and 2. The tunnel brace in steps 3 and 4 was also installed. The main brake lines were then installed as described on page 28iS/U-05 step 1. Some other parts of the upper fuselage also got some attention. All of the steps separating parts on page 29iS/U05 had been completed earlier. The strut attach angle was fabricated and match-drilled according to steps 1 and 2 on page 29iS/U06. When moving on to step 3, a misreading of the instructions resulted in machine countersinking the wrong side of F-1202M-L. A new part has been ordered.

  Oct 21, 2023     Weeks 27 & 28 - (50 hours)       Category: Fuselage

It has been a busy two weeks with work accomplished on several fronts. The assembly and installation of fluid fittings begun last time and described on page 27iS-02 was completed. The fuel tank was successfully pressure tested using the procedure outlined on page 26iSU-08. The fuel tank and two floor plates, 01229-1 and 01229A, were installed, match drilled, and nutplates added completing steps 5 through 9 on that page. When mounting the fuel tank we found that it is a very tight fit. There is no room for the washer that is supposed to go between the top sides of the fuel tank and the fuselage side as shown in the detail drawing. Meanwhile, the many parts for the forward upper fuselage were prepped with Cortec. The first seven steps on page 29iS/U-03 were completed attaching parts along the upper edge of the upper firewall. Work also continued on the rudder and brake pedals. A match drilling error resulted in one brake pedal not lining up with the others. We ended up ordering a new part and re-doing it which was complicated by the fact that the outer hole was already drilled to full size leaving no pilot hole for match drilling. A lot of time was spent lining things up and finding ways to hold everything in place for drilling. The final solution involved a small drilled hole, a cleco, and a drill press.

  Oct 07, 2023     Week 26 - (35 hours)       Category: Fuselage

Picking up from where we left off last week, work continued on page 24iS/U06. The fuel pump bracket assembly, which had been started earlier, was completed and then match drilled to the left baggage bulkhead. It was then removed, de-burred, and nutplates added completing steps 5 though 12. Filling two holes in the right bulkhead finished step 13 and the page. The steps on page 24iS/U-07 involve the assembly and installation of the rear baggage bulkheads and all of the parts attached to them. Dimpling for nutplates and fluting the lower edges of the bulkheads completed the first three steps. Most of bulkhead assembly is then brought together in step 4. This is a complicated step and should be looked at very carefully. There are many specific overlaps and places where multiples layers are riveted together. We made the mistake of not including the bulkhead layer when first installing nutplates in 01207D-L&R. Luckily this was caught early and quickly corrected. In steps 5 through 8 the overhead bridge piece between the roll bar and the rear bulkhead was assembled and installed. Finally, the Fuel Pump Bracket Assembly was reattached in step nine, completing the page. The F-12109 assembly on page 24iS/U-08 was completed earlier. That left only its installation in step 4. The seat backs, which were mostly completed last week, were finished by installing the seat back brace assembly and the adjustment pins and springs detailed on 25iS/U-05 and 06. We were able to skip most of section 26 since we opted to purchase a finished fuel tank. We began with steps 1 and 2 on page 26iS/U-07, assembling one of the supply/return fittings. Before moving any further and pressure testing the tank we did a brief test fit of the tank in the fuselage. We put off doing anything more in order to let the sealant cure. Looking at section 27, we began the process of assembling fluid fittings and the fuel valve bracket assembly as outlined in steps 1 through 6 on page 27iS-02. Meanwhile, we had a couple of our newer members begin work on the Rudder Pedal and Brake System. First the rudder pedal blocks were cut and formed as outlined in step 1 of page 28iS/U-02. The pedals and blocks were then temporarily clamped together as described in step 2. Brake pedal torque tubes were then added to lock both rudder pedals in the neutral position completing steps 3 and 4. A pair of brake master cylinders were then temporarily attached in step 5. Brake pedals were then added and clamped to the rudder pedals with the whole assembly vertical and perpendicular to the work table in step 6, finishing the page. Holes were then match drilled through pilot holes connecting the brake pedals with the brake pedal torque tubes as described in step 1 of 28iS/U-03. Then a #12 drill was used to final drill all the way through the matched assembly in step 2.

  Sep 30, 2023     Week 25 - (20 hours)       Category: Fuselage

Two projects got some attention this week. The missing bulkheads arrived. They were prepped and work began on parts that are mounted to them. Meanwhile, parts for the seat backs were located and prepped. Then work began on them as well. For the seat backs, preparing parts in steps 1-3 on page 25iS/U-02 was done last week. Hinges for the seat back brace assembly were fabricated and installed on the brace plates as outlined in steps 1 through 4 and 7 through 11 on page 25iS/U-03. (Steps 5 and 6 had been done earlier.) The matching hinge halves were then match drilled and attached to the seat backs in steps 1 through 4 on page 25iS/U04. The heavy frames were added to the seat backs as detailed in steps 5 through 7. Then the adjusting hardware was installed in step 8. The seat back brace assemblies were then attached to the seat backs by fabricating and installing matching hinge pins as directed on page 25iS/U-05. Meanwhile, the first four steps of 24iS/U-06 were completed, match drilling and attaching the F-12110 plate to the left aft bulkhead. Assembly of the fuel pump bracket was next. Steps 5 through 7 were completed which nearly finished the bracket. Our work this week was somewhat limited by the airport aviation day open house. We hosted a pancake breakfast and had aircraft and projects, including the RV-12, on display. We talked to a lot of people, but didn't get a lot of work done.

  Sep 23, 2023     Week 24 - (35 hours)       Category: Fuselage

Thanks in part to tropical storm Ophelia, we had a slightly smaller group working on the RV this week. Still, we got a lot done. Work began with going back to steps 11, 12, and 13 of 24iS/U-02. These steps had been skipped last time due to lack of a #43 drill bit. The switch mounting hole was match-drilled, the backing holes in the roll bar were final drilled to #30 and then the switch plate was tapped to #4-40. This completed page 24iS/U-02. The installation of the canopy latch block was next on page 24iS/U-03. A template was first used to match-drill holes in the bottom edge of the roll bar. Three of the holes were then countersunk and tapped #8-32 for screws. The canopy latch block was then countersunk for the screws and installed. This completed steps 1 through 6. Meanwhile, steps 7 though 13 were also completed, preparing parts and assembling the roll bar supports, finishing that page. The roll bar was then clecoed in place once again in the first step of 24iS/U-04 along with the two support assemblies. The twelve holes on each lower side of the roll bar were then match drilled into the heavy 1231D brackets. The entire assembly, including the brackets, was then removed and de-burred. Everything was then reinstalled and permanently riveted in place. Finally, the bolts for the heavy brackets were torqued and torque seal applied. The last step, unrelated to the others, was to final drill #19 two holes in the aft flange of the left baggage floor. We ran into a problem on the next page, 24iS/U-05. We couldn't find the two 01207C bulkheads. After much searching, we concluded that we never got them, even though we had checked them off on our inventory sheet. We discovered that we had instead two extra 01207D parts which must have been mistaken for the missing 01207Cs. With so many parts having similar numbers it is not a hard mistake to make. We ordered the two bulkheads and will have them next week. In the meantime, we prepped and primed all the parts that are called out on page 24iS/U06 that will be attached to the bulkheads. Similarly, nutplate rivet holes were dimpled and some holes machine countersunk in parts as called out on page 24iS/U07. The first three steps of page 24iS/U-08 were also done completing the F-12109 assembly. Also completed was the installation of the cowling hinges detailed on page 23iS/U-09.

  Sep 16, 2023     Week 23 - (35 hours)       Category: Fuselage

The main focus of this week's sessions was the rollover structure beginning with 24iS/U-02. It took a little while to figure out the puzzle of how all the roll bar components go together. There was a lot of checking, examining the plans, and rechecking before anything got put together. Of particular note are the F-1231E plates. Only one is shown on the illustration and it would be easy to leave the forward one out of the structure. Once we were satisfied that all was understood, the roll bar assembly was clecoed together. The heavy 12321D brackets were prepped in step 2 and then loosely bolted to the airframe in step 3. The roll bar assembly was then clecoed to the brackets in step 4. Steps 5 and 6 involved final drilling and match drilling holes in the roll bar and C-01213A latch piece. Everything was then disassembled and de-burred. The holes in the outer flanges of the roll bar assembly were then machine countersunk along with the holes in C-01213A and specific holes in the face of the roll bar. Steps 11, 12, and 13, which involve part 01231F-2 were temporarily skipped because we lacked a #43 drill bit. The bit will be ordered and those steps completed next time. The roll bar assembly was then clecoed back together and then riveted together as directed in steps 15 and 16. Meanwhile, work continued on installing the lower cowl hinges, following the steps on page 23iS/U-09. The directions were followed exactly, but the fit of the hinges is not precisely as illustrated. There is about 1/16 space between the edge of the skin and the row of hinge tabs. That may require more investigation.

  Sep 09, 2023     Week 22 - (40 hours)       Category: Fuselage

The side skins and related structures were the main focus this week on the fuselage. The skins continued to be prepped while work resumed on 23iS/U-05. Arm rest tabs were match drilled and de-burred. Then the arm rests were riveted in place at directed in steps 3 and 4. The longerons were then fitted along with the canopy decks and clecoed in place, which completed the steps on 23iS/U-05. By this time prep work on the skins outlined on page 23iS/U-06 had been completed. The process of installing the skins was then begun with the steps on page 23iS/U07. Meanwhile, as a separate project, work was also begun on the small vent door assemblies detailed on page 23iS/U-08. Small triangular reinforcements were first riveted to the forward vertical structure in step one of 23iS/U-07. Then the skins were fitted. The longerons, canopy deck, and skins were clamped together and match drilled. Specific holes were then machine counter sunk and the entire assembly removed and de-burred. The bottom and aft edges of the skins were “broken” (edges curved inward slightly), nutplates were added, and the rear tabs were removed. The skins were then reinstalled and tape was used to cover holes that were not to be riveted at this stage. After carefully reviewing the rivet and countersink call-outs on page 23iS/U-10, riveting was begun starting with the cherry max rivets. Near the end of skin riveting the vent doors were added and the rear side stiffeners installed. This completed 23iS/U-07 and U-08. While the riveting was taking place, some time was spent preparing for the steps on page 23iS/U-09. The lower cowl hinges were located and cut to size, completing step one on that page.

  Sep 02, 2023     Week 21 - (30 hours)       Category: Fuselage

The week began with finishing the process of altering the two longerons by opening one end by 5.4�nd then twisting that end by 2.7�Once that was finally accomplished, the longerons were completed by match drilling and clecoing the F-01234 canopy deck plates to them. This completed all steps on page 23iS/U-02. Meanwhile, the roll bar attach plate was prepped by completing steps 1 and 2 on page 23iS/U03. The installation of the mid fuselage brace was then begun adding parts 01205A, 01205B, 01205C as outlined in steps 3 and 4. The narrow seat back adjustment plates were then added to the brace as described in step 5. We were a little confused at first which way they faced, but fortunately an experienced RV-14 builder stopped by who set us straight. This completed all steps on page 23iS/U03. The two F-01204J plates were carefully identified by side and then machine countersunk. They were then riveted to the existing structure completing steps 1 and 2 of 23iS/U-04. Steps 3, 4, 8, and 9 simply involved separating parts, riveting the arm rest brackets, and removing a tab from the arm rests. Meanwhile, holes were dimpled in the canopy decks and the corresponding holes machine counter sunk in the longerons as described in steps 6 and 7 which completed 23iS/U-04. Four vertical braces, 1202E and 1203G, were then riveted to the structure completing the first step on page 23iS/U-05. Meanwhile, looking ahead to 23is/U-06, the process of prepping the side skins was begun. The inside surface of the left skin was primed with Cortec. Then the tedious task of enlarging the opening for the wing spars was begun. That concluded our sessions for the week.

  Aug 27, 2023     Week 20 - (30 hours)       Category: Fuselage

It was a busy week with a lot of interruptions, but still good progress was made on the RV-12. The week began with the first steps of page 22iS/U-05. Parts were scuffed in preparation for the application of tank sealant. Then the lower firewall, bottom plate, and console sides were riveted together as outlined in steps 2 and 3. The seven nutplates were also added along the bottom edge of the center firewall/bottom plate. It was then time to add tank sealant. This is messy stuff. First it has to be mixed and then carefully applied where directed. Once mixed it cannot be stored for any significant amount of time, so any remaining sealant must be thrown away. Seems a waste considering the small amount that is used for these steps. The shelf was then riveted to the top flange of the firewall with the sealant between them. Sealant that was squeezed out in the process was cleaned off with acetone. The sealant remains very sticky for a long time and parts have to be handled carefully. Thoroughly nasty stuff. The two diagonal stiffeners along with the 00088A&B bracket were installed onto the firewall as described in steps 6 through 9. The first step of page 22iS/U-06 added curved skins to the sides of the forward assembly. Then the small cowling attach plates were installed on the curved surface of the forward edge of the firewall as outlined in steps 2 through 5. The next step, on page 22iS/U-07, was to turn the fuselage over and attach the completed forward assembly. This completed the 22iS section. 23iS/U-02 involves the strange exercise of making changes to the two longerons. The aft ends of the longerons were first trimmed. Then came the challenge of opening the 90�ross section of the longeron by 5.4�This involved the use of a vise and a 1/2 inch socket to progressively force the heavy angle open. We only got one longeron opened to the correct angle as described in step 3. The rest of this process will wait until next time. (On Thursday we were interrupted by the arrival of a Rans S-12xl that had been donated to the chapter. Two of our members had journeyed all the way to Houston Texas to get it. We helped unload the aircraft and then on Saturday spent time during our session reassembling it. Once inspected, the plane will be sold as a fundraiser for the chapter.)

  Aug 19, 2023     Week 19 - (30 hours)       Category: Fuselage

This week began with the attachment of a fuel tank pad to the aft center section bulkhead which completed the final step of section 21iS. All of the steps on page 22is/U-02 involved separating and preparing parts and were quickly completed. Page 22is/U03 began easily enough with dimpling and the installation of yet more nutplates onto the F-01201C-1 lower firewall bulkhead. Steps 4 through 8 also went smoothly, assembling F-01257-1 brackets and nutplates to the F-01201B-1 shelf. It was step 3 that gave us trouble. The isometric view confused everyone who looked at it. The result was that we machine countersunk the wrong side of the F-01272-1 plate. We called in our resident A&P expert who fabricated a set of small doublers that would provide the necessary material thickness to properly countersink and rivet from the other side according to the directions. With that problem solved, we moved on to page 22iS/U-04. The focus of this page is the assembly of the console. Holes were countersunk and dimpled according to the directions in the first three steps. A step drill was used to enlarge the holes called out in step 4. Then the WE-1204 brackets and F-12131 stiffeners were final drilled and riveted to the F-01217 console sides and nutplates installed. Step 8 completed the page with the riveting of the console sides to the F-01272-1 floor plate. Page 22iS/U05 requires the use of fuel tank sealant along the firewall seams. We ordered sealant, but it has not yet arrived. So looking ahead the assembly on that page was test fitted, but not riveted. Parts for the following page were also located and primed. We also took a look ahead to 23iS/U-02 which involves what appears to be a challenging task of fabricating the longerons.

  Aug 12, 2023     Week 18 - (45 hours)       Category: Fuselage

This week started with the first steps of 21iS/U-19. This involved separating and preparing the six sets of fuselage corner skins. Everything so far has been internal parts and we have been routinely priming everything with Cortec. Unfortunately, we applied Cortec to both sides of the corner skins, so the primer will have to be removed from the outer sides. Need to begin watching more carefully what is interior vs. exterior. Nutplates were added to the two F-01275F skins, then the skins were riveted to the existing structure which finished all the steps on that page. Parts were separated and de-burred according the steps on page 21iS/U20 with the exception of the F-12113 plate which is not installed on the iS version. Attention then turned to the bottom skin on page 21iS/U21. The access holes were dimpled and nutplates riveted in place. The F-00020 plate was also riveted to the skin. Six system block studs were lubricated and then installed through the skin finishing all steps on that page. The edges of the bottom skin were “broken” (slightly curved inward) and then the skin was clecoed to the structure. The six F-1204Z braces were then clecoed in place by reaching through the structure to align each one. Next, the six triangular F-1268 doublers were clecoed in place and then both braces and doublers were riveted to the skin. Tape was added to cover holes that were not to be riveted and then, with the help of some of our younger members, the skin was riveted to the fuselage structure. Tasks on page 21iS/U23 began with dimpling the two F-01213 floor plates, again assisted by our younger crew. Nutplates were added then the fuselage assembly was turned right side up and the floor plates riveted to the structure. The final step in attaching the floors proved tricky. Nutplates had to be installed in the top flange of the F-01202 bulkhead which had been rendered nearly inaccessible by installation of the floors. By reaching through lightening holes and slightly lifting floor corners, the nutplates were finally installed. Parts were separated and de-burred completing all steps on that page. Moving to the rear of the fuselage, 21iS/U-24 involved attaching a plate to the rear ribs and adding brackets and snap bushings. Holes were first dimpled for nutplates and the nutplates installed. The F-12108A bracket was then riveted to the F-01207B-1 plate. The plate was then clecoed onto the rear ribs and then brackets, F-01286A-L&R, were riveted through the plate into the ribs. The bracket assembly was completed by riveting the two F01286B-L&R parts to the existing F-01286A bracket. Snap bushings were then installed. The final step of that page and of the entire section involves attaching a fuel tank pad. We haven't done that step yet. Next time.

  Aug 05, 2023     Week 17 - (35 hours)       Category: Fuselage

Work continued on the cabin structure this week with page 21is/U11. The right seat floor was riveted in place similar to the left seat floor done earlier. The two floor assemblies were then riveted to the center section bulkhead. Step 4 was also completed, bolting a 1204R plastic block to the frame. Another plastic block was then bolted to the structure in step 1 of page 21is/U12. The next steps involved riveting plates to the vertical members of the center section bulkhead, 1204H and 1204B. Rollers were then added to the lower ends of those members (1204M). Parts were separated and prepped in steps 1 and 2 of page 21is/U-13. The remaining steps on that page involved preparing another bulkhead for adding to the structure. Holes in the bulkhead were countersunk and some were enlarged. At either end parts 1203C, 1203B, and 1203D were riveted to the bulkhead. More parts were added to the 01203A-1 bulkhead on page 21is/U-14. 1203E parts were separated, riveted to each other, then riveted to the bulkhead. Further work on the bulkhead continued on page 21is/U-15. 1203J parts were separated and riveted onto the bulkhead. Nutplates were also added. The completed 01203A-1 bulkhead was then installed onto the cabin structure in the first two steps of 21is/U-16. 01226 plates were then added to either end of the structure in steps 3 and 4, followed by the installation of nutplates in step 5. Tasks on page 21is/U-17 began with a time-consuming and somewhat difficult job of separating then precisely tapering a set of heavy L brackets. The finished brackets were then riveted to four “step ribs” to form two step rib assemblies. The first steps of page 21is/U18 involved the complicated process of attaching the step rib assemblies to the 01203A-1 bulkhead and adding the smaller 01202F bulkhead to the the front of the rib assemblies. (There are many, very specific instructions in that process.) The final steps on page 21is/U18 were to add a number of snap bushings plus a fairlead to the overall structure. This required turning the structure over to more easily get at the bushing locations.

  Jul 30, 2023     Week 16 - (36 hours)       Category: Fuselage

Good progress continued this week on the RV-12 fuselage. The first tasks were those on page 21is/U-05. Completing for now the baggage compartment bulkhead assembly, steps one through five were done, including the installation of the bearing bracket assemblies. The entire bulkhead assembly was then set aside. The pulley bracket was assembled in steps six and seven. Then the complicated flaperon mixer arm was assembled completing steps eight through twelve. Page 21is/U06 began with separating and deburring a number of small parts. The eight seat ribs were then numbered and the small parts attached to some of them, completing part of the right seat rib assembly. More work on the seat ribs continued on 21is/U-07. Holes were drilled and dimpled, nutplates added, and the F-1269 plate installed. Page 21is/U08 was also completed by installing the pulley bracket assembly to ribs #5 and #6 along with the flaperon mixer arm assembly to ribs #3 and #4. Continuing to page 21is/U09, nutplates were added to two sets of F-01267 A-1 and F-01267B-1. Then those parts were installed between ribs #2 and #3 and between ribs #6 and #7. The final page of the week was 21is/U10. This involved preparing the seat floors for attaching to the rib assemblies by dimpling and adding nutplates and then installing the floor for the left seat. So six pages of good progress in one week.

  Jul 23, 2023     Week 15 - (28 hours)       Category: Fuselage

In spite of some more interruptions, steady progress was made on the RV-12 this week. Picking up where we left off, the first task was assembly of the ELT bracket followed by riveting of the bracket to two of the baggage ribs. This completed all of the steps on page 21isU-02. Continuing on to 21isU-03, the baggage ribs were riveted to the assembly and nut plates installed according to the plans. The baggage bulkhead was then assembled which included riveting the stub spar plates to either end, dimpling holes along the top edge, and installing nut plates. Completing 21isU-03, nut plates were riveted to two square baggage ribs. Moving on to 21isU-04, bearing bracket assemblies were riveted together. The baggage bulkhead was then added to the assembly along with the four square short ribs. Nut plates were also added to the baggage floors. The final step on 21isU-04 was to trim and separate an L bracket. That was where we ended for the week.

  Jul 17, 2023     Week 14 - (45 hours)       Category: Fuselage

A lot was accomplished on the RV-12 this week. This was partly due to an extra session that took place while waiting all day for the wing kit to arrive. Work continued to be focused on the main center section spar carry-through. Step 8 on 20isU-03 was completed after some discussion and research on the meaning of the directions which seemed to contain a double negative. The skin stiffeners were then added, completing all steps on 20isU-04. Next came the skin attach flanges and aft side bulkheads on page 20isU-05. All of those steps were completed. It was then on to the next section. Fuel tank pads were cut and riveted. Holes were dimpled and nutplates installed in the baggage floors. The floors were then riveted to the main center section assembly. This completed steps 1 through 6 on 21isU-02. In the middle of all of this the wing kit arrived. It came late in the day so we didn't have time to do much with it. The next session may be devoted to inventorying that kit.

  Jul 08, 2023     Week 13 - (20 hours)       Category: Fuselage

This week we finished the hardware inventory and began the first steps in the fuselage build. All of the parts set aside earlier were scuffed, cleaned, and primed with Cortec. Assembly was then begun with the installation of plate nuts. Parts were then match drilled, dimpled, and machine counter sunk according to the instructions. We completed all of the steps on 20iSU-02 plus steps 1 through 7 on 20iS-03. Meanwhile, we've been notified that the wing kit is on the way. It is scheduled to arrive sometime on July 11th.

  Jun 24, 2023     Week 12 - (20 hours)       Category: Fuselage

Finally! The fuselage kit arrived the middle of June, but had to be put aside due to the Ford Tri-Motor visit. On Saturday we began the process of inventorying everything. We're not quite finished the hardware inventory, but everything else was accounted for with only a couple of minor exceptions. We referred to the plans and located all the parts necessary for the first few steps and set them aside. The rest of the parts were organized into plastic bins. In spite of some upcoming interruptions (condition inspections and vacations) we expect to resume build sessions soon.