For those of you who are trying to decide on what airplane to buy, you should first decide on your typical mission. Here are a few statistics:
How does your mission compare?
But, if you just want to have them or must be equipped to fly IFR, then you will be pleased with the panel space available on the Seawind. You will also be pleased that the Seawind is such a stable instrument platform.
WHAT NOT TO LOOK FOR IN A SEAPLANE
Is salt water in your future? If the answer is yes, your options become very narrow.
Salt water and aluminum are not compatible. Even infrequent splashes in salt or brackish water will lead to major corrosion repair in a few years on an aluminum airplane. A fresh water rinse will slow the process, but it will not remove the salt at every rivet or those nooks and crannies.
Now, you should rule out everything but fiberglass.
NOT ALL FIBERGLASS IS CREATED EQUAL
Vinyl ester resin is a hybrid resin with nearly the strength of epoxy, but without the disadvantages. It takes on virtually no moisture (less than 2%). It is compatible with all the fuels and requires no special treatment for the fuel tanks. There have been no recorded health problems in either the aviation or the much, larger boating industry.
So, the main structural item remaining is the fiber.
KEVLAR is a high-priced, hard-to-work-with fabric that is poor in compression. It is not recommended for amphibians unless you are concerned about bullets being shot at your plane.
CARBON FIBER is a high-priced, lightweight fabric. It has a very limited market and limited weaves. As a result, the weaves commonly used in aircraft are very coarse compared to those weaves available in E-glass. So, to acquire a smooth surface, much more filler is required for carbon fiber. That reduces the weight advantage.
THERE ARE MANY MORE DISADVANTAGES
E-glass fabric is most commonly used in the industry, and the most cost-effective. For flying boats, it is the best for a water environment.
To a great extent, the resin and fiber criteria apply to all aircraft, not just amphibians, even though the moisture condition is greatly reduced with land planes.
SPECIFICALLY FOR SEAPLANES
WHAT DO YOU LOOK FOR?
This article was originally written for experimental aircraft.
CARBON/GRAPHITE VS. FIBERGLASS
Surface finishes are applied to reinforcing fibers to allow handling with minimum damage and to promote the fiber to matrix (resin) interfacial bond strength, water resistance and optical clarity. Since graphite is almost exclusively used for aerospace and military markets, where expensive epoxies are utilized, the manufacturer's finishes have been optimized for epoxy. This is the reason that vinyl ester resin is not normally recommended for use with carbon fabrics. Exceptions would have to be tested and close attention to the manufacturer's Certification should be specific regarding the applied finish.
It is very difficult to properly wet out graphite woven cloth, because there is little change in appearance when resin is introduced. Since carbon is opaque even when completely wetted out, visual inspection for air inclusions is impossible. This makes inspection either very difficult or expensive (ultra-sonic equipment) and reject rates are unquestionably high. The danger is in what you can't see. For that reason (and others related to aerospace requirements), the most common fabrication process for carbon parts is elevated temperature curing, performed with expensive epoxy prepregs.
To fabricate a graphite part, epoxy resin impregnated, graphite fabric reinforcements, core, peel-ply, breather ply (perforated sheet for resin control), and bleeder cloth (for excess resin and a vacuum path) are placed into or on a prepared mold, covered and sealed with a thin impervious sheet of plastic material, drawn down with vacuum, placed into an oven, and cured at high temperature (typically 250°-270°F) for several hours under precise controls. A standard for many years in the aerospace industry, this process presents many negative issues relating to cost, handling and quality control, making it practical only for the military, the aerospace industry, and a few other specialized and high priced products (sporting goods, race cars, etc.).
After it is manufactured, shipping and storage of the prepregs in a frozen-state also requires a high degree of quality control. The material has a limited storage life but, most importantly, a short out-life. This means that after bringing the material up to room temperature in sealed storage bags (to avoid moisture, one of prepregs' major problems), the clock starts ticking.
Carbon fiber has the highest specific stiffness of any commercially available fiber and very high strength in both tension and compression. It's impact strength, however, is lower than glass with particularly brittle characteristics being exhibited by high modulus fibers. The graphite laminate tends to shatter, with very sharp, stiff needles and shards around damaged edges. The racing industry must provide crash "cages" of Kevlar to protect the drivers from dangerous pieces.
Like metals, graphite is opaque to radio signals. Antennas cannot be installed within the carbon skins, so they must be attached outside, interrupting the smooth, flowing, composite surface and, of course, causing drag. Fuselage and wing skins of carbon are normally electrically-grounded to each other with jumper wires, as are the control surfaces to the wing, so that the hinge bearings are not damaged if forced into service as electrical conductors.
Since carbon can be greatly affected by corrosion due to galvanic reaction, special care and time must be taken to insulate dissimilar metals, e.g., aluminum, steel, brass, etc., from the carbon. This would involve placing a sacrificial piece of fiberglass between the graphite laminate and all metal hinges, brackets, tracks, etc., and dipping rivets, bolts screws, and bushings in primer resin before installation.
Surface finish of a prepreg is extremely porous. Epoxy resin has an affinity for moisture, as does the freezing and thawing process, and any moisture lay-up will produce water vapor (steam) under vacuum and elevated temperature, which is evident in the finished part as porosity, a rejection factor. The solvents used in the manufacturing (prepregging) process can also produce voids during curing. The predetermined resin quality is sufficient to wet-out the fibers but not to fill in the coarser graphite fabric weave patterns. That process is left for the builder to do — squeegee filler into the porous surface and sand. Then repeat the process for any remaining pinholes. Some of the weight-savings is certainly lost with the addition of fillers.
Expensive honeycomb core materials and film adhesives, used to bond the core to the face sheets, require additional labor and associated expense. Any assembly of carbon prepreg parts must be accomplished with more expensive structural adhesives, compatible with the graphite/epoxy components. If the ribs, bulkheads, webs, etc. are attached or reinforced with a wet lay-up process, graphite fabric and epoxy must be used and, again, a good visual inspection will be impossible. Be careful — epoxies are toxic and could cause serious and lasting reactions. Dry graphite fabric must be handled with more care than fiberglass. Fibers can break and loose particles can be inhaled. Also, cured carbon splinters will not work their way out of the skin as would glass or wood.
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