MIL-S-83318A(USAF)
After the specified exposures the panels shall be cooled in the fluid for 24 hours at standard conditions. The peel strength shall be measured within 10 minutes after removal from the test fluid. Two 1 inch (25 mm) wide strips shall be cut through the sealing compound and fabric to the metal and extended the full length of the fabric. The specimens shall be
stripped back at an angle of 180 degrees to the metal panel in a suitable tensile testing machine having a jaw separation rate of 2 inch (50 mm) per minute. During the peel strength testing, three cuts shall be made though the sealing compound to the panel in an attempt to promote adhesive failure. The cut shall be at approximately 1 inch (25 mm) intervals. The results shall be the numerical average of the peek loads during cohesive failure. Failure of the sealant compound to the fabric shall not be included in the peel strength values.
TABLE III. Peel strength panels
Quantity |
Panel Material |
Panel Thickness |
|
4 4 4 4 4 8 |
Aluminum alloy QQ-A-250/13, T6 Aluminum alloy QQ-A-250/12, T6 chemical treated in accordance with MIL-C-5541. Stainless steel MIL-S-5059, compositio 304 finish 28 Titanium MIL-T-9046, type I, composition 8 Aluminum Alloy QQ-A-250/12, T6, chemical filmed in accordance with MIL-C-5541. Aluminum Alloy QQ-A-250/12, T6, chemical filmed in accordance with MIL-C-5541. Coated with material conforming to MIL-C-27725. |
0.040 inch (1.00 mm) 0.040 inch (1.00 mm) n 0.025-0.040 inch (0.60-1.00 mm) 0.025-0.040 inch 0.60-1.00 mm) 0.040 inch (1.00 mm) 0.040 inch (1.00 mm) |
20
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