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Split Nut to Hold Cables for Nicopress
Source: 2002-Q4 Beartracks
The photos show a use for a split nut. These are available from most electrical supply houses. The split nut is made of copper so it should be soft enough not to damage the cable once tightened.

Use the split nut to hold your cable to length while you squeeze or crimp the nicopress. As soon as you have one press fixed you can remove the split nut and finish squeezing to set. Use your cable trimmers to cut off the excess tail from the cable. These little gadgets are inexpensive and it is handy to have a couple around the shop.

Engine Choices Part V- Fuel Metering and Ignition
Source: 2002-Q4 Beartracks, Mike Meador and Bob Barrows
Sometimes it is difficult to put into words (particularly written words) that which you know. To transfer knowledge that has taken many years to acquire in a few short paragraphs is not a skill that I have mastered very well. I marvel at other writers’ ability to take a difficult subject and make it understandable to me. It would be easy to give yourself a list of part numbers and say “Here you go! Assemble it according to the manual and you should be OK.” Stuff made today is almost idiot-proof, but, I am an example that they are making better idiots every day. I thought that this series of articles would serve to show you how easy it is to put together your own engine. Instead it has served to be a list of generalizations that can only steer you in the right direction to a destination- mainly the perfect Bearhawk engine.
In this final installment, let’s discuss fuel delivery systems and various ways to light your fire.
As you already know, the Bearhawk will operate via gravity flow for a carburetor, so no fuel pump is needed. If a fuel injection (FI) system is desired you will need not one pump, but two: the mechanical pump attached to the engine, and an electrical boost pump for backup. FI systems are more expensive, and as a result of needed fuel pumps, weigh more than a carburetor. The main advantage of FI over carburetor (for the Bearhawk application) is the difficulty in developing intake, or carb ice. FI is expensive, and can run as much as $1000 more than a comparable carburetor, and that does not include the extra fuel pumps!
There is a middle ground between the two systems called a pressure carburetor. It requires a fuel pump but has a lot of the advantages of FI system that are not really needed on a Bearhawk. The ability to fly inverted is not something that I think you will need to be doing very much of anyway.
The ideal Bearhawk engine will take advantage of the “free” gravity flow and use a carburetor. The limitation of carb ice is something that you should have been trained to deal with in your flying lessons. There are devices that can warn you when ice is building up, or you can keep your manifold pressure gauge (if so equipped) in your instrument scan. A slow drop in manifold pressure during cruise indicates a building restriction due to possible carb ice. Most carburetors are shop rebuildable, where as the FI system needs very specialized tools and training to work on. Finally, the carburetor is the most cost-effective way to deliver the fuel/air mixture to the cylinders. We are in the business of keeping it simple, and carburetors do just that.
The final systems to consider are the ignition systems. Up until recently you really only had the choice as to what brand of magneto you wanted to install. There are now several different types of electronic and mechanical systems that you can choose from. There is a reason that the magneto has reigned supreme for nearly 100 years- it works. Any electronic ignition system (EIS) that you choose must have a built-in redundancy to prevent engine failure. The main disadvantage of the magneto is that once you have set your timing it is set for good regardless of power setting. With the exception of startup (due to impulse coupling) you are locked into the advance you set the mag at. This is where the EIS really prove their worth- variable timing. Another advantage of the EIS is a much hotter spark that results in an improved flame front and better fuel burn. Currently Unison Industries (Slick) is considered to have the most advanced EIS on the market.
The Slick system is actually two magnetos with a piggy-backed electronic ignition built in. In effect you have four ignition sources- sounds like a lot of sparks. The Slick system is certified and is available to home builders. There are at least two other non-certified EIS available. So far the results have been generally good, and that is promising. Most of the engines that we ship out of our shop that have an EIS also have one old-fashioned magneto for backup.
Another system that looks intriguing uses miniature catalytic converters to light off the fuel/air mixture; it has no moving parts. I’ll take a wait and see approach- in other words, you go first.
That about wraps up your Bearhawk engine. As you can see you have a bewildering number of choices. So I would like to present you with what I consider to be the perfect Bearhawk engine. The following listing has been worked up with the Bearhawk in mind:
- Lycoming O-360 set up to burn auto fuel
- Narrow Deck
- Angle Valve Cylinders
- Conical Mount
- Rear Entry Oil Sump (with adapter)
- Constant-Speed Prop Setup (need governor drive)
- Rebuilt Bendix Magnetos
- Rebuilt Carburetor
- Maybe a Vac. Drive for a Mini Alternator
- Aluminum-Steel Gear One Piece Oil Pump
This is nearly the exact engine on the prototype Bearhawk. It is relatively inexpensive to build and a brute of an engine. The angle-valve head keeps things cool during those long climb outs and the large valves let it breathe a lot easier.
Avipro Wing Load Testing
Source: 2002-Q4 Beartracks, Bob Barrows

Wing was loaded with sand bags at 30% chord line average. Sand load approximating air load distribution from the root to the tip. Wing deflection and observed skin distortion was recorded for loads from 900 to 6000 pounds. Tip deflection at 6006 pounds was 3.378″ at main spar and 4.521″ at rear spar. Load was removed and wing showed no signs of bending or twist. Some small distortion was observed at the center butt rib near the rear spar. Also a slight distortion on wing top skin in gas tank bay area. The 6006 pounds represents a loading of 5.7g at 2500 pounds gross weight, as adjusted for the weight of the wing and 30 gallons of fuel. The test was continued to 6774 pounds, at which point the main spar failed at the top cap strip in a buckling mode, 30 inches in from the 3/8 inch wing attach to fuselage bolt. The 3/32 inch rivets failed in shear that attach the top .032 root skin to the rear spar flange.
Note of interest: up to the 3003 pound test loading the fuel tank had not been installed. This left the top skin in the fuel tank area supported only by the .025 hat sections to control skin deflection. Skin deflected inward about 1/2″ and caused wing twist. After loading was removed, no wing distortion was observed. Top skin basically went back to its original shape. Wing failure occurred at 6774 pounds, or 6.4g. No permanent wing deflection or twist was observed up to 5.7g. The rated aircraft max allowed load is 4.5g at max gross weight.
Recommended Inspection of Completed Wings:
Check relationship of fuel tanks to top skin at stiffeners. Push on top skin at stiffeners, and skin should not deflect more than 1/16″ before contacting fuel tank. Readjust tank straps or shim between tanks and stiffeners as needed with silicone rubber.
Running changes to be made to the wing as a result of tests, for plans serial number 583 and up:
1. .032 Center ribs rear lightening hole to be changed from oval to round (drawing #6).
2. Hat-shaped top skin stiffener to be 5/16-3/8 inches high .050 5052H32 (or 6061T6) aluminum. These materials form easier and will be stiffer (drawing #2).
3. Main spar front top cap strip (1/8×1-1/4) will be made longer so as to butt up against front spar plate at root end (drawing #3).
4. Center root end rib will be doubled up with opposing flanges, ribs riveted together at .025 support angles, and .032 spar attach angles (drawing #2 and #6).
4. Rivets attaching .032 root skin to rear spar flange to be AN426-4 (drawing #2).
It is important to note that none of the listed running changes are mandatory, but seemed to be worthwhile, considering the knowledge we gained from the test and the small extra weight, cost, and effort required when constructing the wing.
Pat Fagan Final Assembly
Source: 2002-Q4 Beartracks, Pat Fagan

Pat Fagan in Pearblossom CA has assembled his Bearhawk and is awaiting final inspection before flight testing. He sent in a couple of photos of the delivery and assembly at his airport. Pat has promised to send in more photos of the assembled aircraft and a write-up of his first flight experience for the next issue of Beartracks.

Tom Yeomans’s Bearhawk
Source: 2002-Q3 Beartracks, Tom Yeomans, #75, Edgewood NM

Hi Bob and Mike, here are a few pictures of the auto-powered unfinished Bearhawk.
The first flight of no. 75 was June 26th, 2002. I don’t have a lot to talk about as far as the flight characteristics of the aircraft itself at this time. Control time spent in the air has been very straightforward with no bad habits to report. The first flights have been short due to engine concerns. During the first flights I was able to do some adjusting of the control systems to get all of the cabling adjusted correctly. The aircraft has a short takeoff run, likes to climb, and a straight rollout in a three-point landing.
The engine is a Ford Duratec 3.0 24-valve engine I have converted myself. I am using a 2:1 belt reduction, electromotive aftermarket ignition/fuel injection, stock Ford injectors, starter, induction, and alternator. Most of the time spent so far has been dedicated to cooling, ignition, and a few mechanical items that do not reflect on the aircraft design at all. I knew going into the auto conversion that I would need to do some changing. I elected to not do an exterior finish until I had all the bugs worked out with the engine. The first flights had the engine sounding good and the RPMs seemed good. During the fifth flight I had an ignition misfire that had me digging into the problem quickly after the flight (I did finish a normal flight). The exhaust was looking very rich and the fuel burn was very low (sounds confusing). No guess at the real horsepower, but can’t be much. I did get a new chip for the onboard computer and offline software.

I have the cooling system temps running under 200 degrees during climb now and the ignition system is very close to a final dial in. I have a little more testing on the ground to do but should be back in the air early September. The fuel burn is now in the 8-GPH range according to the software.
Lessons learned here are, if you want to get in the air faster, talk to Bob about one of his engines, or if you want an auto system without tinkering with your own conversion, look at one of the companies that have lots in the air already. Hope everyone has a great finish to the year and many get their projects flying soon.
Lycoming Engine Choices, Part IV: Cylinders
Source: 2002-Q3 Beartracks, Bob Barrows and Mike Meador
The one area of engine building that offers the most choice of services is the cylinder. You can choose to have your cylinders cleaned and checked and overhauled. You also have the option to buy new. If the cylinder is low-time (less than 300 hours) Continue reading
Bob Marek’s Bearhawk Flight Report
Source: 2002-Q3 Beartracks, Bob Marek

Here are some pictures of 156RM.
Continue reading
Wing Strut End Interference with Wing Skin
Source: 2002-Q3 Beartracks, Tim Babcock, #361, Edmonton AB
Hi Mike, just some news from the north. #361 is progressing nicely. Wings are almost done and I have purchased my O-540 Lycoming with accessories and a constant speed prop. I have all the wheels and brakes, etc. I should be able to start on the fuselage later this summer. I ran into a problem on the wing strut attach fittings. On drawing #15 the strut end at the wing fitting shows a 9/16″ radius from the C/L of a 3/8″ hole. That is fine. On drawing #15a (supplied with the new strut material ordered from Bob) this same area shows a 3/4″ radius from the C/L 3/8″ hole. This fitting hits the bottom of the wing before it can reach line up with the holes in the attach bars. I made a set of attach bars a little longer to allow the holes to line up. I will adjust the strut to make the dihedral work out. I haven’t noticed anything in the newsletters regarding this problem. If you can check that would be great. I don’t think changing the radius on the aluminum bar is a good option.
Mike replies: I checked with Bob and he has suggested builders fabricate piece to drawing and check for fit. If needed, up to 1/16″ of material can be removed on a flat to allow for no interference with wing skin. As with any plans-built there will be slight variances between each builder’s parts. Bob has designed plenty of extra strength in the airplane just for such occurrences.
Tail Wire Threading Die Guide Tool
Source: 2002-Q3 Beartracks, Bill Cox #303 Baytown Texas

Here’s a tool for concentric threading of tail wires using a die. Continue reading

