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' November 29, 2018 <br /> No conditions were identified where Class I Division 2 boundary greater than 5 <br /> feet was required, and this margin was applied at all locations defined by paint <br /> application. <br /> Based on the analysis the following boundary limits are recommended: <br /> Vertical above low bay stackers <br /> The distance from the aircraft to the 2% LEL boundary predicted by the <br /> CFD analysis varies by location but a distance of 2.5 feet was found to be <br /> conservative for the fuselage. Applying an additional 2.5 feet for plume <br /> dispersion results in a Class I Division 1 boundary of 5 feet for the <br /> fuselage. These boundaries were applied for the entire fuselage <br /> regardless of the predicted %LEL—these %LEL values are noted below to <br /> indicate the degree of conservatism this approach applies. <br /> A vertical plane at 5 feet above the crown of the aircraft had no solvent <br /> concentrations above 1%LEL. This was determined to be an appropriate <br /> boundary for Class I Division 1, with 5 additional feet for Class I Division 2 <br /> Vertical above high bay stackers <br /> The distance from the aircraft to the 2% LEL boundary predicted by the <br /> CFD analysis varies by location but a distance of 2.5 feet was found to be <br /> conservative for this area. Applying an additional 2.5 feet for plume <br /> dispersion results in a Class I Division 1 boundary of 5 feet. <br /> A vertical plane at 5' above the vertical fin had no solvent concentrations <br /> above 0.2%LEL. This was determined to be an appropriate boundary for <br /> Class I Division 1, with 5 additional feet for Class I Division 2 <br /> Horizontal adjacent to the nose of the aircraft <br /> Airflow adjacent to the nose of the aircraft indicates %LEL values do not <br /> exceed 0.5% at 5 feet from the nose. This was determined to be an <br /> appropriate boundary for Class I Division 1, with 5 additional feet for Class <br /> I Division 2 <br /> Horizontal adjacent to the stabilizer <br /> Ventilation of the horizontal stabilizer is not as effective as the fuselage. <br /> As a result a larger distance was required for this area. The boundary for <br /> this region was simplified to enable quicker assessment in the field. The <br /> boundary for Class I Division 1 was placed 5 feet south of column 14 <br /> (where the maximum %LEL was predicted to be less than 0.8%), and the <br /> boundary for Class I Division 2 was placed at column 14. <br /> Adjacent to engines <br /> The inboard and forward regions for the engines are defined by open <br /> container requirements. The outboard region is defined by the decorative <br /> (1-6ge 8 of 10-) <br />