Van's Aircraft RV-8 Construction Manual
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Van's Aircraft RV-8 Construction Manual

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VAN'S
RV-8/8A
CONSTRUCTION
MANUAL
VAN'S AIRCRAFT, INC.
14401 KEIL ROAD
AURORA, OREGON USA
503-678-6545
FAX 503-678-6560
www. vansaircraft.com
support@vansaircraft.com

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  • Page 1 VAN’S RV-8/8A CONSTRUCTION MANUAL VAN’S AIRCRAFT, INC. 14401 KEIL ROAD AURORA, OREGON USA 503-678-6545 FAX 503-678-6560 www. vansaircraft.com support@vansaircraft.com...
  • Page 3 SECTION 1 INTRODUCTION RV AIRCRAFT RV AIRCRAFT SECTION 1 INTRODUCTION TABLE OF CONTENTS NOTE: SECTION 1 INTRODUCTION SECTION 2 DESIGN PHILOSOPHY Van’s Aircraft Inc. kits are carefully designed and tested. They will demonstrate performance very close to quoted figures with the engines and propellers recommended. Van’s Aircraft SECTION 3 TOOLS AND WORKSPACE recommends that the kits only be assembled according to the supplied plans.
  • Page 5 RV builder to join or form one whenever possible. (A list of Builders Groups and contact persons is available MAINTENANCE, REPAIR, from VAN'S AIRCRAFT.) Building an airplane is a big undertaking, and a builder should never be too proud or ALTERATION OF AIRFRAMES, POWERPLANTS, Avery Enterprises individualistic to take advantage of what others have to offer.
  • Page 6 The RV-8/8A retains all the advantages of tandem seating, but the roomier cockpit and second baggage Before getting into the construction details of your RV, let's take a look at the design philosophy and goals that compartment make cross-country travel more comfortable and practical.
  • Page 7 VAN'S AIRCRAFT, INC. SECTION 3: TOOLS AND WORKSPACE While building an RV requires some investment in special tools, most builders with home workshops already own many of Rivet Cutter: Needed for shortening rivets when the exact length rivet is not available. Not used too often, a good pair of wire snips the basics.
  • Page 8 VAN'S AIRCRAFT, INC. Protractor/Carpenters Level: A bubble protractor can measure the Tubing bender: Although there are not a lot of aluminum tubes in the RVs, those that are there need to be bent properly. Fuel angle of any surface from a horizontal or vertical reference plane. The carpenters level (2-3 ft. in length) is lines, pitot lines etc.
  • Page 9 VAN'S AIRCRAFT, INC. CATEGORY ITEM Required/Optional CATEGORY ITEM Required/Optional Drills/Countersink/Taps 1 #3 Drill Bit Dim pling/Riveting Dimple Die-Reduced diam. (3/8” diam.) 3/32" Female Dimple Die #10 Drill Bit Dimple Die-Reduced diam. 1/8” diam Female Dimple Die REQ FOR RV-14 #11 Drill Bit Dimple Die Set 1/8"...
  • Page 10 Safety Glasses 1 Roll Duct Tape Caliper (6") Dial or Digital 1 Kit Fuel Tank Test Kit - See Van's Aircraft Catalog Edge Rolling Tool 1 Roll Masking Paper - 24" Hand Seamer 1 Sheet Sandpaper - 60 Grit - 8.5X11 Sheet Screw driver Bits - Size #2 2 Sheet Sandpaper - 80 Grit - 8.5X11 Sheet...
  • Page 11 The derivation of the word "Homebuilt'' is obvious, and most of us have heard stories of airplanes being built in various models. Thus, most 800 series numbers are for the RV-8, 1000 series numbers are for the RV-10, 1200 series numbers for basements or attics where the walls had to be knocked down to get them out when finished.
  • Page 12 VAN'S AIRCRAFT, INC. Center Line: Used for the center line of 1 1/2 [38.1] holes, tubes, discs, and any other part which is symmetrical on each side of the R3/4 [R19.1] center line. This is a series of long and short dashes.
  • Page 21 To prime the inside of pushrods with liquid primer, pour primer into one end and swirl it towards the other end, coating the entire Van's Aircraft does not have an "approved" primer. We use Sherwin Williams P60G2. This is used on the Quick-Builds (QBs) and inside surface.
  • Page 22 VAN'S AIRCRAFT, INC. 5.1 ALUMINUM PRIMING & PAINTING (continued) PAINTING Painting an airplane obviously adds to its weight. The amount of weight depends on the type and amount of paint, primer and Historically not many manufacturers primed the interior of their products, but there are still many flying 50 year old airplanes without surface filler used.
  • Page 23 VAN'S AIRCRAFT, INC. 5.2 EDGE FINISHING, HOLE DEBURRING & SCRATCH REMOVAL The finishing procedures just described will constitute a sizable portion of the total building time. However, they are important for structural reasons as well as cosmetic. Aluminum sheet of the 2024-T3 variety is relatively hard and brittle. Maintaining the high strength of this material in use requires Most of these holes, edges, etc.
  • Page 24 VAN'S AIRCRAFT, INC. FLATTEN TOP 5.3 MARKING PARTS REMOVING RIVETS & REMOVE BEVEL To avoid the possibility of deforming thinner material when WARNING: NEVER use a scribe to make layout lines or other marks on aircraft parts. Due to removing a rivet, modify a pair of long handled side engine vibration part failure can occur along these scribe lines.
  • Page 25 VAN'S AIRCRAFT, INC. FIGURE 1: RIVETING PROCESS,NOMENCLATURE & COMMONLY Artwork by Tony Bingelis ENCOUNTERED PROBLEMS. 01/17/14 RV-ALL 05-05 DATE: REVISION: PAGE...
  • Page 26 VAN'S AIRCRAFT, INC. FABRICATING THE WEDGE TOOL The wedge tool provides assistance when blind riveting in locations where it is not possible to align the tool and the rivet. The wedge tool(s) will be placed between the rivet and the riveting tool enabling the riveting tool to pull the rivet from an angle, yet still achieve a properly seated manufactured head.
  • Page 27 VAN'S AIRCRAFT, INC. 5.4 (continued) PROPER INSTALLATION HOLE SIZE RIVET DRILL DIAMETER SIZE Step 1: Verify tool and CHERRYMAX rivet compatibility MIN. MAX. CHERRYMAX RIVET INSTALLATION by performing a test on an easily removed rivet, in the event that removal becomes necessary. For removal - 4 (1/8")[3.2mm]...
  • Page 28 VAN'S AIRCRAFT, INC. Where the skin thickness is insufficient, the countersunk hole for the rivet head enlarges the original rivet hole and no longer supports the shaft of the rivet. Only a portion of the rivet head is now contacting the skin, so it cannot achieve its design strength which is based on full head contact.
  • Page 29 VAN'S AIRCRAFT, INC. 5.6 BACK RIVETING 5.7 FOLDED TRAILING EDGES The shape of control surface trailing edges affects the "feel" and performance of the aircraft's controls. When riveting thin aluminum skins to light ribs or stiffeners, it is difficult to avoid getting some slight indentations in the skin around This cannot be over stressed.
  • Page 30 VAN'S AIRCRAFT, INC. For adjusting buldged trailing edges fabricate a squeezing tool like the one shown in Figure 4. Join two 1X2X6 hardwood blocks with wire springs made from welding rod or left over hinge pin. The wire will help maintain the block's alignment. Note the 5.7 FOLDED TRAILING EDGES (continued)
  • Page 31 VAN'S AIRCRAFT, INC. 5.8 RIVETED TRAILING EDGES Scenario B: Both skins already in place: With the skins and wedge prepared as described in scenario A, insert the wedge between the skins. Use several clecos to hold the wedge to one of the skins and maintain alignment.
  • Page 32 VAN'S AIRCRAFT, INC. Check constantly for any deformation of the trailing edge. If deformation over 1-2 in. [2.5-5 cm] in length is observed place blocks near the curved area and lightly bend the trailing edge back down. Take your time and work as precisely as possible. An excessively wavy or bowed trailing edge will affect the flying qualities of the airplane.
  • Page 33 VAN'S AIRCRAFT, INC. 5.9 ROLLED LEADING EDGES 5.10 LAP JOINTS Before the empennage control surfaces can be installed on the stabilizers, the leading edges must be When riveting a lap joint, the expansion of the aluminum caused by the setting pressure and the expansion formed.
  • Page 34 Steel parts should be primed and painted immediately after cleaning to prevent rust. Stainless steel will quickly dull cutting tools (drills, deburring tools, reamers, etc.). Use plenty of lubricant (Van's Aircraft uses Boelube) and keep the cutting speed low. Use a step drill if creating holes over .250 [6.4 mm] in diameter.
  • Page 35 VAN'S AIRCRAFT, INC. 5.16 INSTALLING NUTPLATES 5.17 FUEL TANK SEALANT Nutplates are almost always installed with flush rivets. When the structure is too thin to machine countersink there are two options. The recommended sealant, MC-236-B2, (often called ProSeal) is available through the The first alternative is to dimple both structure and nutplate.
  • Page 36 Like welding, fiberglass molding is a specialty skill. Fiberglass parts lend themselves more to production methods than do most other parts. Thus, VAN'S AIRCRAFT offers most fiberglass parts pre-molded. To make the parts that are not supplied in the kit any...
  • Page 37 Clamping a piece of wood behind the acrylic material and drilling through into the wood can eliminate chipping on the backside of adverse effect. It is the cumulative affect that will cause shortened service life of your canopy. The use of a Van's Aircraft Canopy drilled holes.
  • Page 38 VAN'S AIRCRAFT, INC. FASTENERS AS PIVOT POINTS 5.20 NUT AND BOLT TORQUES In specific cases, bolts are intended to be used as axis of rotation. The most common example is the attachment of control system cables. Here, it is intended that the cable end fitting pivot on the bolt. In these instances, the nut must not be torqued to the standard torque value.
  • Page 39 VAN'S AIRCRAFT, INC. 5.21 ELECTRICAL D-SUBS ELECTRICITY PLUG-IN There are three primary units of measure or terms to know to successfully wire the aircraft: voltage, current and power. The battery SIDE we will be dealing with is known as a 12V battery. Batteries in good charge will have a terminal voltage between approximately 12.8 and 13 volts.
  • Page 40 VAN'S AIRCRAFT, INC. 5.21 ELECTRICAL (continued) SHIELDED WIRES Some wires included in the kit are shielded BACKSHELL ASSEMBLY CONDUCTOR WIRE with braided wire surrounding the main conductor wire(s). Unless otherwise stated all There are a number of connections which make use of d-sub assemblies sheathed with a...
  • Page 41 VAN'S AIRCRAFT, INC. TERMINAL 5.21 ELECTRICAL (continued) TOO LOOSE INSULATION INSULATION CRIMP AT WIRE WIRE END OF TERMINAL ELECTRICAL CONNECTIONS BARREL WIRE INSULATION NOTE: Terminals should be crimped, but not necessarily soldered. If a METAL termination is soldered, the wire should be supported near the solder joint to...
  • Page 42 VAN'S AIRCRAFT, INC. 5.21 ELECTRICAL (continued) Strip the wire according to the WIRE STRIP LENGTH found in Table 1, then use the crimp tool. TERMINAL INSTALLATION TABLE PART WIRE STRIP RECOMMENDED NUMBER NOMENCLATURE LENGTH CRIMPING TOOL TOOL USE NOTES ES-00003 MOLEX PIN .093...
  • Page 43 VAN'S AIRCRAFT, INC. 5.21 ELECTRICAL (continued) Strip the wire about 3/32". Note that I've shortened the insulation grip FIGURE 4 wings on this pin. These connectors are designed for automotive applications where wiring insulation is MUCH larger in diameter than OPEN BARREL TERMINALS for the same AWG size in aircraft wire.
  • Page 44 VAN'S AIRCRAFT, INC. 5.21 ELECTRICAL (continued) OPEN BARREL TERMINALS (continued) Now you can install the pin into the connector's housing. In Figure 1 you can see the barbs that snap out to keep the pin from being pulled backwards through the hole. The stop tabs will bottom out in the hole from behind to keep the pin from coming on through.
  • Page 45 ELECTRICAL TROUBLESHOOTING Audio NOTE: Van's Aircraft has tailored each avionics component for the combination of aircraft and avionics by supplying each Basic Checks: component with a specific set of default presets. Although not supplied in the kit a list of these presets are available upon request.
  • Page 46 Solution: Check that all headsets are in stereo mode. If the left and right channels are shorted together with a mono headset it will one at a time (for example autopilot, transponder, com radio, ADS-B, GPS, etc...) Although Van's Aircraft has done their best be impossible to change the left or right volume level for any stereo item such as aux music or EFIS warnings.
  • Page 47 VAN'S AIRCRAFT, INC. 5.21 ELECTRICAL (continued) Problem: A random static noise comes through the headset. Problem: My EFIS warning tones are too quiet I can't change the sound levels using the audio mixer on the control module. Solution: Adjust the volume and squelch on the intercom and determine if this will make the noise disappear. If the noise can be Solution: Check that your headsets are turned to stereo not mono mode.
  • Page 48 VAN'S AIRCRAFT, INC. 5.21 ELECTRICAL (continued) Glossary of Electrical Terms These definitions are not meant to be “scientifically” correct but rather a definition understandable to someone not technically familiar with electrical systems. Problem: My EMS display values randomly spike causing warnings.
  • Page 49 VAN'S AIRCRAFT, INC. 5.22 COMPRESSION FITTINGS IN PLASTIC TUBING 5.24 DRILLING, TAPS AND DIES Install compression fittings to plastic tubing using the Material alloy and hardness, as well as the makeup of the cutting tool determine the speed at which metal is following steps: best drilled.
  • Page 50 VAN'S AIRCRAFT, INC. 5.24 DRILLING, TAPS AND DIES (continued) 5.26 HARDWARE REFERENCE SOME NOTES ON TAPS A "tap" is a tool used for cutting internal threads into an existing hole. Taps come in several styles. The most common hardware store variety is a four-flute tap. The flute is the groove along the length of the tool. When using a...
  • Page 51 VAN'S AIRCRAFT, INC. FLUSH HEAD PROTRUDING HEAD AACQ-4-3 5.26 (continued) AACQ-4-4 AACQ-4-6 AD-41-ABS AD-41H AD-42H FIGURE 2: NAS1149 AND AN960 WASHER SUBSTITUTION AD-62-BS NAS1149 washers may be used anywhere a AN960 washer is called for. However, DO NOT use a AN960 washer where a NAS1149 washer is specified.
  • Page 52 VAN'S AIRCRAFT, INC. 5.27 FLUID FITTINGS FIGURE 1: ROD-END BEARING REFERENCE CHART PIPE THREAD FITTINGS PART NO. STUD BEARING HOLE LENGTH THICKNESS Many fittings used in RV plumbing systems have tapered pipe threads. Tapered pipe threads have an 5.26 (continued) outside diameter which decreases toward the opening.
  • Page 53 VAN'S AIRCRAFT, INC. 5.27 FLUID FITTINGS (continued) NOTE: Fitting depictions are intended for general identification purposes only. All threads, except for those at or adjacent to flared ends, are tapered NPT threads even though they may not be shown tapered.
  • Page 54 VAN'S AIRCRAFT, INC. 5.28 CONCLUSION The manual now changes from general information to specific building instructions for your new airplane. The information is presented in logical, step-by-step order. This DOES NOT mean that the construction sequence given is the only way to do things; depending on factors such as available help, available space, or just personal preference, you might well alter some procedures with good results.
  • Page 55 SECTION 6 : EMPENNAGE RV-8/8A RV-8/8A SECTION 6 : EMPENNAGE SECTION 6: EMPENNAGE Drill/match-drill all the holes inboard of the HS-00006/HS-00005 rib attach points (See View A-A). DO NOT drill the holes that will attach the HS-00006 and HS-00005 ribs or the holes outboard of the bend line. The holes outboard of the bends will be drilled later, after the bends are made.
  • Page 56 SECTION 6 : EMPENNAGE RV-8/8A RV-8/8A SECTION 6 : EMPENNAGE Remove the HS-00006 and HS-00005 ribs and flute as necessary between the rivet hole marks. Rivet the HS-609PP bars to the HS-603PP spar channels. The rivet callout is correct on the plans. See Section 5.4.
  • Page 57 SECTION 6 : EMPENNAGE RV-8/8A RV-8/8A SECTION 6 : EMPENNAGE Trim the flange of the stiffener (surface perpendicular to the skin) to fit inside the tapered rudder. Single Cleco the ribs to the front and rear spars. notches on the edge of the stiffener note the beginning points of these trim cuts. Trim the stiffeners and clean up the edges with a file and the Scotchbrite wheel (See R-815 (A-H) Detail).
  • Page 58 SECTION 6 : EMPENNAGE RV-8/8A RV-8/8A SECTION 6 : EMPENNAGE TRIMMING THE STIFFENERS Drill the remaining holes in R-713 and R-801PP to final size. The E-701-L/R elevator skins and E-720 (A-L) elevator skin stiffeners are provided with pre-punched holes. The various E-720 stiffeners are snipped from the pre-punched lengths of aluminum angle.
  • Page 59 SECTION 6 : EMPENNAGE RV-8/8A RV-8/8A SECTION 6 : EMPENNAGE and E-709. ribs from the spar. Drill the E-701-R skin to the understructure. Place the E-714 counterweight on the forward end of E-703 and E-704 as shown (See View F-F, DWG 5).
  • Page 60 SECTION 6 : EMPENNAGE RV-8/8A RV-8/8A SECTION 6 : EMPENNAGE Lay a square reference along the trailing edge of E-701-L in the trim tab cutout (where E-606PP attaches). Clamp the inboard end of the tab with the bending blocks to the edge of a table (See Figure 6-1) Use double- sided tape between the mating surfaces of the bending blocks and the trim tab skin to help prevent the wedge Mark the bend line perpendicular to the aft edge of the E-701-L trim tab cutout.
  • Page 61 SECTION 6 : EMPENNAGE RV-8/8A RV-8/8A SECTION 6 : EMPENNAGE You can add the fiberglass tips to the completed empennage now or you may chose to wait and do all the fiberglass Sight down the trailing edge of the elevator, with the trim tab in trail. If the tab has any twist and does not work at a later stage.
  • Page 62 SECTION 6 : EMPENNAGE RV-8/8A RV-8/8A SECTION 6 : EMPENNAGE Figure 6-1 Figure 6-4 Figure 6-2 Figure 6-3 REV: 13 6-15 2/25/14 REV: 13 2/25/14 6-16...
  • Page 63 SECTION 6 : EMPENNAGE RV-8/8A RV-8/8A SECTION 6 : EMPENNAGE NOTES: REV: 13 6-17 2/25/14 REV: 13 2/25/14 6-18...
  • Page 65 (Tip: cut a #8 screw short so that it enters the K1100 nutplate easily All information necessary to complete the RV-8/8A QuickBuild Kit is contained in the standard Builder’s Manual. and use it to gage the depth.) The empennage, built from the Standard Kit, should be completed before starting the wings and fuselage.
  • Page 66 SECTION 7 RV-8/8A RV-8/8A SECTION 7 The stand (shown on DWG 12A) is simple; two vertical posts run from floor to ceiling. Horizontal arms of steel angle PREPARING THE WING RIBS or wood, bolted to the posts, support the main spar. The size of the posts and arms is not important, but they must You will save time if you set up and prepare all the ribs for both wings at the same time.
  • Page 67 If necessary, file the hole in the correct direction to center it over the tiedown hole, then drill it full size with a Unibit. If you plan to use the capacitive fuel gauge senders offered in the VAN'S AIRCRAFT ACCESSORIES CATALOG you should complete their installation at this point using the instructions supplied in the sender kit.
  • Page 68 SECTION 7 RV-8/8A RV-8/8A SECTION 7 Install the fuel pick-up tube and position it so it lies on the bottom of the tank. construction with adequate ventilation. Use a respirator, gloves (which also keep oil from your skin off the surfaces Check all final details before installing the baffle and closing the tank.
  • Page 69 Rivet the W-702 inboard skins The construction technique for RV-8/8A ailerons (DWG 13A) is similar to that of the elevators. The aileron uses ribs first, because the outboard skins overlap them.
  • Page 70 ATTACHING FLAPS TO THE WING Flap details are shown on DWG 14B. The flaps are the easiest control surfaces on the RV-8/8A to build. The only jigging required is a level, flat surface at least 5' long and 1' wide. Easy or not, it is possible to build in an There are two good methods of installing the flap hinge pin.
  • Page 71 SECTION 7 RV-8/8A RV-8/8A SECTION 7 trailing edge on the tip. Remove the tip and lay out the rivet lines (top and bottom) 5/16" from the edge. Cleco the W-715-1 tip back on the wing and slip the W-412 tip rib back in place. The flange edge must be flush with the tip edge.
  • Page 72 SECTION 7 RV-8/8A RV-8/8A SECTION 7 NOTES Fig.7-11. The VA-112 drain flange riveted to the outside of the tank skin. Fig. 7-8. The interior of the tank at the outboard end. The T-410 reinforcement helps seal around the nose. The blob on the rib is a 316”...
  • Page 73 F-801A-1 Firewall. For ease of tooling and forming, larger RV-8/8A bulkheads and fuselage ribs are formed in two or more pieces and ‰ Machine countersink the #30 rivet attach holes on each F-801L Backing Plate for a flush head on the fwd side then riveted together to form the complete part.
  • Page 74 Cleco the F-867C-1 Attach Angle, and the F-867D-1 Stiffener to the F-867A-1 Cooling Air Ramp (See “Cooling RV-8 COOLING AIR RAMP ASSEMBLY Air Ramp Assembly Exploded Iso View”, DWG 61A). Final-Drill all 3/32 holes in the cooling air ramp to #40.
  • Page 75 DWG 62). the previous step. ‰ RV-8 FORWARD FUSELAGE SUB STRUCTURE Reinstall the WD-813-1 Bolt Weldments with all the bolts as depicted on DWG 62. NOTE: Two of the bolts in each WD-813-1 Bolt Weldment are not installed at this time.
  • Page 76 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE Stiffener and the bottom edge of the F-866A-1 Lower Fwd Baggage Bulkhead. Bulkhead, between the holes, to make them straight and flat. Deburr the edges of both bulkhead parts (DWG 63A).
  • Page 77 RV-8A Only: Place the WD-821 Landing Gear Weldments in their approximate positions on the F-804A-2 Center ‰ RV-8 only: Install 12 AN4-11A bolts (six on each side) in the 1/4 holes on the F-804A-2 Center Section Fwd Section Fwd Bulkhead Subassembly (See “Landing Gear Weldment Detail”, DWG 67A). The lower outboard Bulkhead Subassembly, that were left open for attaching WD-821-L-1 &...
  • Page 78 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE ‰ Cleco the F-804C-AL and -AR Center Section Aft Bulkheads to the F-804B-2 Center Section Aft Bulkhead. Temporarily install 1/4 NAS bolts through the bolt holes to insure alignment. Fwd Control Mount, the two F-804L-1 Seat Belt Attach Lugs, and the two F-804M Seat Belt Lug Spacers using the bolts specified in the “Center Section Assembly”...
  • Page 79 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE ‰ time. Repeat the previous three steps for the F-814A-L-1 Fwd Left Inboard Seat Rib Assembly. The only difference being a second F-814HPPX in place of the F-814J Fwd Seat Belt / Vent Anchor.
  • Page 80 ‰ Mark a rivet center line on the F-844-L & -R (RV-8) or F-898-L & -R(RV-8A) Auxiliary Longerons as shown on marked edge on each gusset so that it will nest in the flange bend radius of the F-804C-FL and FR Center Sec- tion Fwd Bulkheads, on the Center Section Assembly.
  • Page 81 If you are going to install the optional Rear Seat Throttle, Refer to DWG OP-2 and the other documentation supplied with the RV-8 Rear Seat Throttle kit. Cut a slot between the two index holes in the F-860B-L-1 Mid Left Arm Rest, ‰...
  • Page 82 It is acceptable to slightly bend the forward pointing brace tube of the landing gear weldment so that the flange of the lower longeron aligns with the doubler plate. JOINING THE RV-8 FWD & MID FUSELAGE SUBASSEMBLIES ‰...
  • Page 83 Prime the two F-811B-1 Stab Attach Bars and the F-811C-1 Angle. Prime the F-811A-1 & E-1 Bulkheads if/as desired. ‰ RV-8 Only: Mark the vertical position of the WD-409 Tail Spring Mounts top edge on the front side of the F-812 Bulkhead Assembly (See “Section View A-A”, DWG 73). 8s8PP-1 r1 06/23/11...
  • Page 84 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE ‰ ‰ Cleco together the F-811-1 Bulkhead Assembly as shown in the F-811-1 Bulkhead Assembly view on DWG 70. Cleco the F-818B-L-1 Baggage Rib Angle to the F-818-L-1 Baggage Rib as shown in the “Baggage Rib Assem- Rivet the five rivet locations that join the F-811A-1 &...
  • Page 85 ‰ RV-8 Only: Match-Drill #30, the 1/8 holes in the F-820-L-1 & -R-1 Fwd Side Skins that are common with the F- ‰ Uncleco the upper 6 inches of the left and right F-820-L-1 & -R-1 Fwd Side Skins, F-823-1 Mid Side Skins, and 844-L &...
  • Page 86 NOTE: If you do not have any 3/16 clecos, final-drill #12 a couple matching holes in the front seatback the F-822-1 (RV-8) or F-890-1 (RV-8A) Fwd Floor Panel that are common with the holes in the fwd and aft bot- support and the seat back side plates, then insert temporary bolts to hold the assembly in position.
  • Page 87 RV-8A Only: Unbolt and/or uncleco and remove all unriveted parts that are in place on the Fwd Fuselage Sub ‰ RV-8 Only: Use Detail C on DWG 73 as a full size template to mark the F-828-1 Aft Bottom Skin for the trim- Structure except for the F-843-L-1 & -R-1 Lower Longerons.
  • Page 88 RV-8A Only: Dimple countersink the #40 holes in the F-8100B-1 Angle, and F-8101C-1 Angle that are common ‰ RV-8 Only: Machine countersink #30 for dimples, the five #30 holes in the tab at the fwd end of the F-889-L-1 with dimpled countersunk holes in the F-891-L-1 & -R-1 Fwd Side Skins (DWG 68A). Dimple Countersink #40, &...
  • Page 89 Bulkheads, that are common with dimpled holes in the cockpit rails. ‰ RV-8 Only: Rivet the five holes at the top end of the F-802C-L-1 & -R-1 L. G. Box Webs to the F-887-L-1 & -R-1 Upper Longerons (See “Fwd Fuse Side Skins and Structure”, DWG 67).
  • Page 90 811-1 Bulkhead Assembly” , DWG 70). Rivet all but the bottom hole in each stab attach bar. Cleco the WD- place on the fwd fuselage (DWG 67 & 68 for RV-8 or 67A & 68A for RV-8A). Refer to DWG 82 & 83 (for an RV-8) 409 Tail Spring Mount and any shims made when it was previously fitted, in place on the F-811 Bulkhead As- or DWG 82A (for an RV-8A), and the FUEL SYSTEM &...
  • Page 91 F-817-L-1 & -R-1 Seat A RV-8 or 8A with a Lycoming IO-360 Angle Valve engine should have the battery installed at the aft loca- tion.
  • Page 92 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE ‰ ‰ Final-Drill #40, the 3/32 holes common between the F-850-1 Bottom Skin and the F-802K-1 L.G. Fwd Cross- Rivet the F-802K-1 L.G. Forward Crossmember to the F-822-1 Forward Floor (DWG 61). Rivet the two nut- member, the F-802L-1 L.G.
  • Page 93 Fwd Fuse Side Skins And Structure view, and Landing Gear Weldment Detail view on DWG 67A. Fwd Fuselage Bottom Skin (See “Exploded Iso View”, DWG 61A). Cleco the F-867C-1 Attach Angle to the F- 802U-1 Crossmember. IF BUILDING WITH A RV-8 OR 8A QUICKBUILD FUSELAGE KIT, BEGIN CONSTRUCTION HERE. ‰...
  • Page 94 Forward Floor Panel is level laterally and longitudinally. A finished RV-8 stands tall when it's on its wheels. The exact "best time" to permanently mount the landing gear will ‰ File a small radius on the corners of the U-801-L & -R Gear Legs so they nest flush in the U-804 Inboard Main depend on the exact assembly sequence you choose, available help and workspace, etc.
  • Page 95 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE ‰ will depend on the exact assembly sequence you choose, available help and workspace, etc. Don't be in a hurry to Deburr the edges of the F-832A-1 Front Seatback get it on the gear -- we have found it much more convenient to keep the top longeron of the fuselage at "navel ‰...
  • Page 96 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE ‰ Deburr the holes in all the parts of the Rear Seatback Assembly. board aft corner of each block as installed. Temporarily bolt each flap bearing block in position using the aft hole locations.
  • Page 97 ‰ Dimple countersink all the #40 holes in the F-830-1 and F-831-1 Seat Floors for flush heads on the top surface. RV-8 CONSOLES AND SEAT RAMP ‰ Dimple countersink all the #40 holes in the F-830B-1, C-1, D-1, E-1, & F-1 Floor Stiffeners.
  • Page 98 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE ‰ step. Remove the F-864E-1 Cable Anchor from the F-864A-1 Throttle Quadrant Mount. Deburr the #30 holes in the cable anchor that were drilled in the previous step. ‰ Machine-countersink the hole drilled in the F-878-L-1 Mid Cabin Brace in the previous step for flush screws on the top surface.
  • Page 99 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE ‰ ‰ Prime the F-8113A-L-1 & -R-1 Mid Cabin Covers and F-8113B-L-1 & -R-1 Console Side Ribs if/as desired. Prime the F-864E-1 Cable Anchor, F-8100B-1 Throttle Quadrant Cover, and F-8100A-1 Throttle Quadrant Mount if/as desired.
  • Page 100 Reattach the right elevator by first inserting the 1/4 bolt in the VA-146 Flange Bearing and then inserting tempo- ‰ RV-8 Only: Mark the location of the three bolt holes used to attach the bottom of the vertical stab spar to the rary bolts at the two outboard hinge locations.
  • Page 101 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE ‰ ‰ Insert a VA-101 Threaded Rod End into both ends of the F-841 Pushrod. Drill #30 the eight rivet holes in both Use a file or sander to progressively remove material from the ends of both bronze bushings. Remove material ends of the pushrod while remaining within the edge distance dimension shown in “F-841 Pushrod Assembly”,...
  • Page 102 If you are using the optional ground adjustable rudder pedals refer to DWG OP-3 (for RV-8) or OP-3A elevators and rudder at maximum deflection.
  • Page 103 SECTION 8 THE FUSELAGE RV-8/8A RV-8/8A SECTION 8 THE FUSELAGE ‰ Install a blind rivet in the #30 hole. Mount the bottoms of the brake master cylinders to the WD-816 Rudder Slide (See “Isometric View”, DWG 81). ‰ ‰ Put the WD-804-L & -R Rudder Pedals in place on the WD-816 Rudder Slide (See Exploded Reference View”...
  • Page 104 ISO Views on DWG 82. ‰ RV-8 Only: Install the vent line bulkhead fittings in the fuselage side and orient them as shown in “View E-E”, ‰ RV-8A Only: Secure the right tank fuel line to the inboard brace tubes of the WD-821-L & -R Landing Gear DWG 82.
  • Page 105 Final-Drill #30 the 1/8 holes common between the F-825-1 Aft Top Skin and the two F-858-1 Shoulder Harness clamp them to the F-802E-L-1 & -R-1 L.G. Box Web (RV-8) or the aft side of the F-802R-L-1 & -R-1 Fuselage Anchors.
  • Page 106 Clips to the F-820-L-1 & -R-1 Forward Side Skins. Reinstall the two temporary screws in the side of the F- ‰ Bond the Vent SV-1 NACA Hose Interface in place on the F-820-L-1 Fwd Side Skin (RV-8) or F-891-L-1 (RV- 803A-1 Instrument Panel.
  • Page 107 Machine countersink the #40 holes in the F-873F-1 Angle. ‰ Rivet the F-803D-L-1 & -R-1 Clips to the F-820-1 (RV-8) or F-891-1 (RV-8A) Forward Side Skins (See DWG 74 ‰ Dimple countersink the #30 holes in the outboard flange of the F-873D-1 Baggage Door Inner Skin and the cor- or 74A).
  • Page 108 / twist it slightly to get a flush fit on the fuselage. Once satisfied with the fit, secure the Skin and the F-820-R-1 (RV-8) or F-891-R-1 (RV-8A) Forward Side Skin. Verify that the door is flush with the door in place on the fuselage using duct tape around the perimeter.
  • Page 109 ‰ RV-8 Only: Make the bend adjustments required so the F-863-1 Tank Attach Brackets fit flush with the fuselage side skins and the T-405 Angles on the fuel tanks as shown in the top view of “Wing/Fuselage Junction”, DWG ‰...
  • Page 110 ‰ RV-8 Only: The two open holes in the F-820-L-1 & -R-1 Fwd Side Skins are the bolt hole locations for attaching Swing the left flap into its up position while inserting the F-847 Flap Pushrod through the hole in the fuselage the F-863-1 Tank Attach Brackets .
  • Page 111 Install a nutplate on each F-863-1 (RV-8) or F-863A (RV-8A) Tank Attach Brackets as shown in “Section A-A”, the hole in the top flange of the wing spar, will have to be machine countersunk after the nutplates are at- DWG 80.
  • Page 113 Using a #40 bit, drill the four forward most holes in each C-803 canopy rail per View X-X, DWG 44. Do not The RV-8 uses a large bubble canopy that affords excellent all around visibility. The windshield is fixed to a drill the two aft holes in C-803 as these will be match drilled from existing holes in F-816.
  • Page 114 After you have your RV-8 finished and flying, you may want to recall this nuance of the canopy latching function. Use the right combination of sliding speed and arm muscle to fully “seat” the canopy closed before FITTING THE CANOPY SKIRT engaging the latch.
  • Page 115 SECTION 9 FITTING THE CANOPY SECTION 9 FITTING THE CANOPY RV-8/8A RV-8/8A radius gage to find the contact points around the front of the windshield, and bring it around the sides to match up with the top of the canopy side skirts. I usually match the portion that goes over the top, to the NOTES front edge of the roll bar.
  • Page 117 Tapered shims that install between the axle and the gear leg are available through Van’s Accessories Catalog (q Exterior brake lines are fabricated and routed as shown on DWG 45 (RV-8) or DWG C2 (RV-8A). Remember to shim, p/n U-811A, or 1/2q shim, p/n U-811B).
  • Page 118 B and C; the inside radius of the flange on the rear half, the inside of the front half where glass cloth layers overlap, Gear leg fairings on the RV-8 are installed in two phases. The first phase is the fitting of the fairing to the gear leg.
  • Page 119 SECTION 10 ENGINE MOUNT, WHEELS, BRAKES AND FAIRINGS RV-8/8A RV-8/8A SECTION 10 ENGINE MOUNT, WHEELS, BRAKES AND FAIRINGS Use your “sharpie” pen to make four ink “dots” on U-807 where each of the four fasteners will ideally be located. using the molded-in scribe lines and the leading edge parting line as reference points. Smooth the template over Sand away the white gel-coat from the areas where the fairing touches the bracket so the bracket and the ink dots the outside of the fairing and use spring clamps to hold it in place.
  • Page 120 SECTION 10 ENGINE MOUNT, WHEELS, BRAKES AND FAIRINGS RV-8/8A RV-8/8A SECTION 10 ENGINE MOUNT, WHEELS, BRAKES AND FAIRINGS Jack and support the fuselage far enough off the ground that the wheels no longer touch. Set the tail up so the INSTALLING THE WHEEL PANT and U-713C SUPPORT BRACKETS airplane is level at the cockpit longerons (datum line).
  • Page 121 SECTION 10 ENGINE MOUNT, WHEELS, BRAKES AND FAIRINGS RV-8/8A RV-8/8A SECTION 10 ENGINE MOUNT, WHEELS, BRAKES AND FAIRINGS Locate an approximately 1” wide shim thick enough (0.032” to 0.094”) to fit tightly between the U-810 bracket and RV-8A MAIN WHEEL FAIRINGS the brake disc.
  • Page 122 SECTION 10 ENGINE MOUNT, WHEELS, BRAKES AND FAIRINGS RV-8/8A RV-8/8A SECTION 10 ENGINE MOUNT, WHEELS, BRAKES AND FAIRINGS EMPENNAGE FAIRING The following photos and text illustrate how we fabricated the gear leg to wheel fairing intersection fairings on The F-868 and F-8106 empennage fairings are shown on DWG 43. The F-8106 fairing is trimmed to fit as shown, our RV-10 prototype.
  • Page 123 SECTION 10 ENGINE MOUNT, WHEELS, BRAKES AND FAIRINGS RV-8/8A RV-8/8A SECTION 10 ENGINE MOUNT, WHEELS, BRAKES AND FAIRINGS NOTES Top left: Wider layers of glass cloth are applied. A total of four or five layers of 9 ounce cloth works well.
  • Page 125 Installation is straightforward; through the firewall and to the control mount for a nose gear leg, and the landing gear in the RV-8 is mounted in the fuselage.) Because of the arm on the carb. The tandem airplanes use a throttle quadrant, mounted on the left sidewall of the cockpit.
  • Page 126 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION operation where engine cooling is marginal because of limited ram air flow through the engine compartment, INDUCTION AIR INTAKE and because fuel flow volume is low. With a high air temperature and low fuel flow, the fuel has more time to Most RVs are fitted with the filtered airboxes available in Van’s Accessories Catalog.
  • Page 127 The RV-7/7A and RV-8/8A will accept these engines and and have the added option of the 200 hp Lycoming angle valve IO-360. The RV-3 and RV-9A are designed for Lycoming O-235, O-290 and O-320 Most engines with updraft carbs will fit an RV, but some engines have the carb mounted at the very rear engines rated between 118 hp and 160 hp.
  • Page 128 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION protection, usually a tough cast urethane leading edge inlay, rain damage is still a concern. Even a short performance all around at the expense of higher fuel consumption and engine wear. time at reduced rpm in heavy rain will cause enough damage to require refinishing.
  • Page 129 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION ƒ Descents: Constant speed props offer two completely different advantages over fixed pitch props during bolt heads from rotation. descents. First, they can offer added speed during long, slow descents from cruise altitude. With fixed pitch props, power descents are not practical because the added speed causes excessive RPM requiring Quality prop bolts, extension bolts, prop extensions, crush plates, etc., are available through Van’s power reduction.
  • Page 130 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION the ads in magazines such as Kitplanes or EAA's Sport Aviation for prop manufacturers . Call and discuss your needs with them. Don’t be afraid to ask for references. 11-11 11-12 sect 11r8...
  • Page 131 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION 11-13 11-14 sect 11r8 06/24/11 sect 11r8 06/24/11...
  • Page 132 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION 11-15 11-16 sect 11r8 06/24/11 sect 11r8 06/24/11...
  • Page 133 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION 11-17 11-18 sect 11r8 06/24/11 sect 11r8 06/24/11...
  • Page 134 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION 11-19 11-20 sect 11r8 06/24/11 sect 11r8 06/24/11...
  • Page 135 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION 11-21 11-22 sect 11r8 06/24/11 sect 11r8 06/24/11...
  • Page 136 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION 11-23 11-24 sect 11r8 06/24/11 sect 11r8 06/24/11...
  • Page 137 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION 11-25 11-26 sect 11r8 06/24/11 sect 11r8 06/24/11...
  • Page 138 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT RV AIRCRAFT SECTION 11: ENGINE AND PROPELLER INSTALLATION 11-27 11-28 sect 11r8 06/24/11 sect 11r8 06/24/11...
  • Page 139 SECTION 11: ENGINE AND PROPELLER INSTALLATION RV AIRCRAFT NOTES TYPICAL ENGINE PLUMBING DIAGRAM This should be taken as a guide only as it is likely your airplane will vary. TYPICAL INSTALLATION OF A CONTROL CABLE TO THE MIXURE OR THROTTLE ARM The rodend bearing (at the engine end of the throttle and mixture cables) and control arm (on the carburetor) are connected by an AN bolt, sized as necessary, (an AN3 is shown in the example above) with a hole for the cotter pin.
  • Page 141 SECTION 12: FITTING THE COWL, SPINNER & COOLING BAFFLES SECTION 12: FITTING THE COWL, SPINNER & COOLING BAFFLES does not pass over the cylinder cooling fins, or SECTION 12: FITTING THE COWL, SPINNER serve some other accessory cooling function, wasted. &...
  • Page 142 Fit and drill the hinge shown in the Cowling Attach Detail of DWG 43 (RV-4), DWG 63 (RV-6), DWG 45 (RV-7/9), DWG 48 (RV-8), using the holes left open during fuselage construction. Note carefully the details of fitting and propeller…a 3-blade prop will require a longer slot to remove the cowl.
  • Page 143 The resin coat will protect your cowl from grease and grime until you are RV-8 note that one screw in the center of the cover plate attaches it to the U-816 brace.
  • Page 144 SECTION 12: FITTING THE COWL, SPINNER & COOLING BAFFLES SECTION 12: FITTING THE COWL, SPINNER & COOLING BAFFLES The cutout in the spinner cone should match the contour of the prop blade closely. A sliding pin “copycat” ENGINE BAFFLE INSTALLATION contouring tool, widely available at hardware stores, can make the job easy.
  • Page 145 SECTION 13 PAINTING RV AIRCRAFT RV AIRCRAFT SECTION 13 PAINTING MASKING SECTION 13: PAINTING Application of masking tape for color separation and pin-striping is perhaps the most time consuming part of painting. Masking a straight line is tough enough, but getting just the right curve or ‘‘sweep’’ to a line is an art. Common hardware store masking tape usually gives poor results for distinct line separation because it permits too An entire book could be written on the subject of aircraft painting and still leave many questions unanswered.
  • Page 146 SECTION 13 PAINTING RV AIRCRAFT RV AIRCRAFT SECTION 13 PAINTING sect 13.pub 3/5/01 13-3 13-4 sect 13.pub 3/5/01...
  • Page 147 SECTION 13 PAINTING RV AIRCRAFT RV AIRCRAFT SECTION 13 PAINTING sect 13.pub 3/5/01 13-5 13-6 sect 13.pub 3/5/01...
  • Page 148 SECTION 13 PAINTING RV AIRCRAFT RV AIRCRAFT SECTION 13 PAINTING sect 13.pub 3/5/01 13-7 13-8 sect 13.pub 3/5/01...
  • Page 149 SECTION 13 PAINTING RV AIRCRAFT RV AIRCRAFT SECTION 13 PAINTING sect 13.pub 3/5/01 13-9 13-10 sect 13.pub 3/5/01...
  • Page 150 SECTION 13 PAINTING RV AIRCRAFT RV AIRCRAFT SECTION 13 PAINTING sect 13.pub 3/5/01 13-11 13-12 sect 13.pub 3/5/01...
  • Page 151 SECTION 13 PAINTING RV AIRCRAFT RV AIRCRAFT SECTION 13 PAINTING sect 13.pub 3/5/01 13-13 13-14 sect 13.pub 3/5/01...
  • Page 152 SECTION 13 PAINTING RV AIRCRAFT RV AIRCRAFT SECTION 13 PAINTING sect 13.pub 3/5/01 13-15 13-16 sect 13.pub 3/5/01...
  • Page 153 SECTION 13 PAINTING RV AIRCRAFT RV AIRCRAFT SECTION 13 PAINTING NOTES sect 13.pub 3/5/01 13-17 13-18 sect 13.pub 3/5/01...
  • Page 155 Only three moments must be calculated and combined to determine the C.G. position. This figure is of datum is plus (+) and forward of datum is minus (-). In the RV-8/8A, the datum is established at a point that not in itself too meaningful, as the airplane cannot be flown in this condition, but it is important because it forms makes all arms positive (+).
  • Page 156 SOME EXAMPLES Aft limit: 86.82 inches aft of datum Sample 1 shows a typical RV-8/8A loaded with two FAA standard 170 lb. occupants, full fuel, and partial ARMS baggage; the typical beginning of a trip. The airplane is well within both gross weight and C.G. limits, and as shown in Sample 2, remains there even when landing at the end of the trip with minimum fuel.
  • Page 157 SECTION 14 WEIGHT AND BALANCE RV-8/8A RV-8/8A SECTION 14 WEIGHT AND BALANCE RV-8 WEIGHT AND BALANCE CALCULATIONS SAMPLE 2: AS ABOVE, BUT WITH REDUCED FUEL (END OF TRIP) aircraft weighed in a level attitude with oil WEIGHT MOMENT EMPTY AIRCRAFT 1069.00...
  • Page 158 85302.60 SAMPLE 5: BIG PEOPLE, and FORWARD BAGGAGE 76.095 CG = MOMENT DIVIDED BY WEIGHT WEIGHT MOMENT EMPTY AIRCRAFT FWD BAGGAGE 58.51 SEE RV-8 SECTION FOR SAMPLE SITUATIONS 1 THROUGH 6 FUEL 80.00 PILOT 91.78 PASSENGER 119.12 AFT BAGGAGE FLOOR 138.00...
  • Page 159 SECTION 14 WEIGHT AND BALANCE RV-8/8A RV-8/8A SECTION 14 WEIGHT AND BALANCE RV-8A WEIGHT AND BALANCE CALCULATIONS NOTES aircraft weighed in a level attitude with oil A/C registration_______________ Date___________________ Performed by_____________________________________ DATUM (70 inches forward of leading edge) CG RANGE 78.70 inches aft of datum 86.82inches aft of datum...
  • Page 161 Landing Gear: For RV-8 builders, assure compliance with the wheel alignment specification presented in Section Controls: Move and visually check for proper operation. 10 of this manual. If a tailwheel is installed, examine it to see that its pivot axis is vertical, or, preferably, slopes back slightly (trails.) Difficult runway handling often results when the tail wheel pivot axis is raked forward and the tire con-...
  • Page 162 SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT Gas: Check quantities in both tanks and set selector on the fullest tank. feels he needs, concentrating on testing the airplane rather than the engine. An untested engine in an untested airplane doubles the potential for the unexpected happening.
  • Page 163 SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT sometimes even machine gun sounds) The canopy comes open unexpectedly. Obviously these are not the only things that can happen without warning on that first test flight; however, they are PRE FLIGHT PLANNING probably the most life threatening.
  • Page 164 SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT crew on: come too intent on the photography function. The test flight should not be unnecessarily extended in time or geogra- phy just for the sake of getting more photos or video time. Also, proximity of formation flight and/or maneuvers for the cabin door or canopy latching mechanism photo purposes should not be allowed to compromise safety.
  • Page 165 SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT landing speed. EXPANDING THE ENVELOPE Climb out at a shallow angle, easing the flaps up if you used them for takeoff. Start a gentle turn as you pass through Before you fly again, check the conditions in the engine compartment.
  • Page 166 SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT Best Angle Of Climb: After climb tests have been made at normal anticipated speeds, perform timed climbs at indi- Plot Glide Speeds: On the same graph as climb performance, plot points for gliding rates of descent (sink) at vari- cated speeds of 90 IAS, decreasing in 10 mph increments, down to 70 mph.
  • Page 167 C.G. - NEGATIVE The normal loading of an RV, particularly a tandem seat RV-4 or RV-8, results in wide shifts in C.G. position. Aero- WEIGHT STABILITY batics, because the associated unusual attitudes, are much more likely to result in accidental stalls and spins, than is non-aerobatic flight.
  • Page 168 SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT However, pitch control (elevator) forces will be much lighter, increasing the possibility of over controlling. Direction stability in a typical RV aircraft is quite positive. When a hard yaw is induced, the dampening cycles are rather short period—almost difficult to count fast enough.
  • Page 169 SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT Stick free, aileron snatch will result in a rolling tendency. A fixed trim tab will not correct this as it would just push the Another cause of asymmetric stall is airfoil irregularity caused by landing lights in the wing leading edge.
  • Page 170 Van's Aircraft Inc. does not consider spins to be a recreational aerobatic maneuver, and recom- An Alternate Calibration Method: Loran and GPS have given the test pilot another valuable tool in more ways mends that they not be casually undertaken.
  • Page 171 SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT Similarly, assuming that the atmosphere were perfectly stable, when flying at 200 mph, a pilot error of 1/2 degree G-LOAD TESTING pitch attitude will cause a 150 fpm climb or descent rate and several mph speed variation. Thus, great care must be As with flutter testing, G-load testing should be conducted systematically, progressing gradually to higher and higher taken to find smooth air and fly precisely in order that truly accurate speeds be recorded.
  • Page 172 (G-loads) limits, etc. This is particularly important if test- 1600 lb. for the RV-7/7A and the RV-8/8A with the “Dash One” wing (included in all RV-8/8A kits shipped since Janu- ing limits were lower than suggested in this text. There will be a natural tendency for future pilots of this airplane to ary, 2001.) Earlier RV-8/8As with the original wing have an aerobatic gross weight of 1550 lbs.
  • Page 173 SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT SECTION 15 FINAL INSPECTION AND FLIGHT TEST RV AIRCRAFT NOTES IRSPEED ALIBRATION Conditions & Data: 8,000' MSL 42 deg. F. 156 IAS 2675 RPM 20.5'' Man. Pres. Sensenich 68x78 prop E6B computations show that: 156 mph IAS at 8,000' and 42 deg.

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