Max Min Max Min
- 147 141 3733.0 3582.0.0 Length overall:
- 21 ½ 17 ½ 546.0 445.0 Beam:
- ¼ 0.118 6.3 3.0 Thickness of decks and cockpit floor:
- ¼ 0.118 6.3 3.0 Thickness of bottom:
- 1 5/8 25.4 15.9 Sides and bulkhead at front of cockpit:
- 110¼ 98¼ 2800.0 2496.0 Intersection of seat back and floor to pivot pin of steering runner:
- 66 54 1676.0 1372.0 Distance from bow to front of cockpit:
- 96 94 2438.0 2388.0 Stem block length is optional.
- 3 ¾ 2 95.0 51.0 Stem width at bow:
- Stern block length is optional.
- 4 1 ¼ 101.0 31.0 Stern width at stern:
- Seat backs shall be raked aft at an angle of 45 degrees plus or minus 10 degrees. They may be hinged for access to stowage compartment.
- Seat back shall be flat, measuring 11'' (280. mm) in length at the center line, no maximum height, the crown on top of seat must be a minimum of 2'' (50.8 mm) radius with minimum seat width 4''.
- Depth of side panel at each fuselage station shall not be less than heights in the following table:
Layout of Side Panel
Position along side panel starting at bow Minimum Side Panel height Inches mm Inches mm 2 51 2-9/16 65 12 305 3-7/8 98 24 610 5-1/16 129 36 914 6-1/16 154 48 1220 6-7/16 164 60cockpit bottom must be on top of listings. 1524 6-5/8 168 72 1829 6-5/8 168 84 2134 6-1/2 165 96 2438 6-3/16 157 108 2743 5-9/16 141 120 3048 4-5/8 117 132 3353 3-3/8 86 Last Station: 2 inches (51mm) from the stern 2 51
- Side Panels
- Bottom heights of side panels shall not exceed a maximum of 1'' (25.4 mm) above zero line and/or a maximum of 1/2'' (12.7 mm) below zero line. Zero line shall be established by a straight line tangent to stem and stern on bottom.
- Maximum height of side panels above zero line may be 8-1/2'' (215.9 mm) including deck and bottom covering. All heights of side panels shall be proportional to height as shown in “Layout of Side Panel”. The top edge of the side panel may not be concave at any point along its length.
- Hull cross sections must be rectangular from a point 6'' (153. mm) from the bow to a point 6'' (153. mm) from the stern. A maximum 1/4'' (6.3 mm) radius is allowed on the outside top corner of the fuselage where the deck and side panel intersect. Concavities in the deck are not permitted.
- Cockpit floor shall be installed as shown in plans,cockpit floor skin must be on top of listings. The total thickness of the cockpit floor including the bottom skin and cockpit floor skin must be a minimum of 5/8" (15.9mm). A minimum of 2 knees must be installed.
- Structural members such as longerons, stringers, knees, listings, bulkheads, bottom, deck, etc. may be added. Deck may not protrude more than 3'' (76mm) into the cockpit from the bulkhead at the front of the cockpit.
- Design of the internal structure of the fuselage is optional.
- Grab rails may be installed on the inside and/or outside vertical surface of the side panels. They may not extend beyond 8'' (203. mm) from either end of cockpit. Rails shall not exceed 1'' (25.4 mm) in depth or width. Rails are exempted from fuselage measurements.
- Steering post and chock may be inclined in the vertical plane of symmetry.
- Steering shall be accomplished by means of a tiller. Tiller may be of any length ors hape but may not be more than 8 inches (203 mm) wide. Material is optional.
- Either steering rods, cables, or a single push pull link shall be used and shall be positioned beneath the fuselage as shown on the Official Plans.
- Ballast, if used, shall be permanently installed.
- Fuselage shall be constructed of wood only, except as provided in specification A.31. (Sitka spruce is most popular). Fiberglass may be added for reinforcement only. See Interpretations General.
- Sides shall not be hollow.
- Minimum weight shall be 46 lbs. (21 kg) with all hardware, blocks, and tiller.English MetricA full bulkhead must be installed at the front of cockpit.
Max Min Max Min
- 7 3 178.0 76.0 Horizontal distance from the Bow to the pivot point of the front runner:
- National letter and Sail number shall be affixed to each side of the fuselage below the mast stepping point. Color shall contrast with the fuselage and each letter and number shall be a minimum of 5.5 inches (140 mm) high and 0.7874 inches (20 mm) wide
- Foam is an allowed material for the internal construction of the fuselage, reference A.19
See Fuselage Interpretations at the end of the Specifications
- Side Panels