MIL-S-6551A(USAF)
4.4.4 Structural tests. The sample seat shall be mounted on the ejection rails and retained in a test jig by the fitting which receives the catapult trunnion. The seat shall then be subjected to, and be required to withstand without failure, the ultimate loads specified in 3.3.3.1 through 3.3.3.4, inclusive. These loads shall be applied to the seat without cushions. The attitude of the seat during the test may be changed to facilitate testing
if the direction of the loads, with respect to the seat, remains the same.
The loads may be applied by means of hydraulic or pnetuD.atic press, jacks,
shot bags, or any other suitable method. The lap belt and shoulder harness mountings shall be loaded simultaneously to the ultimate loads
specified in 3.3.3.8.1. The lap belt attachment shall be subjected to tests in which the loads are applied to a block or a frame fitted within the seat and held in place by the lap belt attached to the mountings. The block or frame shall be so formed as to cause the belt to pass inward toward the
seat from the mountings to the block or frame at an angle to 20 degrees with respect to the plane of the mountings. The loads shall be applied to the shoulder harness take-up reel by means of a shoulder harness or a strap of equivalent dimensions to the shoulder harness attached to the take-up reel cable terminal. The strap or shoulder harness shall be carried up over the shoulder harness support, and the loads applied as indicated in 3.3.3�8.1.
4.4.5 Ejection test. One test sample seat shall be subjected to a ground firing test in accordance with Specification MIL-STD-846.
4.4.6 Environmental tests. One test sample shall be subjected, in the following order, to each of the following environmental tests:
4.4.6.1 High temperature test. High temperature tests shall be in accordance with procedure I of Specification MIL-E-5272. At the conclusion
) of the test period, and with the seat at the test temperature, the ejection
controls, seat adjustment mechanism, and the shoulder harness take-up reel
control shall function satisfactorily throughout their entire range of operation.
4.4.6.2 Humidity test. Humidity tests shall be in accordance with procedure I of.Specification MIL-E-5272. Upon completion of 120 hours
(5 cycles) with condensation remaining on the seat, the ejection controls,
seat adjustment mechanism, and shoulder harness take-up reel control shall
ftmction satisfactorily throughout their entire range of operation. Upon completion of 360 hours the ejection controls, seat adjustment mechanism, and shoulder harness take-up reel control shall again be tested for
satisfactory operation.
4.4.6.3 Low temperature test. The seat shall be soaked at a temperature of
-67 degrees Fahrenheit (-55 degrees Centigrade) for a minimum of 24 hours. Upon completion of the test period, with the seat at -67 degrees Fahrenheit, the ejection controls, seat adjustment mechanism, and the shoulder harness take-up reel control shall function satisfactorily throughout their entire range of operation.
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