GB548476A - Improvements in or relating to locking pins whereby two parts may be secured in predetermined relationship - Google Patents

Abstract

548,476. Multiple fastenings. FAIREY AVIATION CO.. Ltd., CHAPLIN, H. E., and BOLTON, F. July 29, 1941, No. 9641. [Class 44] [Also in Group XXXIII] A fastening particularly for the folding wings of aircraft comprises oppositely moving pins f connected to the ends of a first-order lever k by pivotal movement of which the pins may be inserted in or removed from apertures formed in pairs of lugs d mounted on the wing stub shown and in lugs b mounted on the folding wing, not shown, the apertures registering when lugs b are sandwiched between lugs d as in Fig. 1, which shows the parts in fastening position. Lugs b and the spaces in which they fit are preferably wedge-shaped and the parts arranged so that pins f are inclined to the horizontal at approximately 30 degrees as shown. Lever k is operated by a link connection o to a sleeve p pivoted at r and having slidably disposed therein a rod q, the parts p, q forming a telescopi'c operating means. The lever k is bifurcated or apertured as seen in Fig. 3 and in the fastened position the rod q is disposed through the aperture with its inner end entered in an annular supporting bracket S. The aperture in lever k is so formed and disposed that rod q can pass therethrough only when lever k is in locking position, and rod q, disposed as in Fig. 1, locks lever k against movement to release position. To effect release, rod q is pulled out to the position shown dotted, Fig. 2, with its inner end clear of lever .k. Parts p, q are then depressed to the position shown in full lines, thus rocking lever k to withdraw pins f. Fig. 2 also shows the lugs b as moved clear of lugs d in the wing-folding operation. Rod q may be held in its inner position by a spring-plunger catch w which must be released before rod q can be pulled out. The fastening and operating means may be disposed in the usual gap between the contiguous faces of the stub and wing, or in recesses in either or both of these parts, and such recesses may be closed by a cover flap t conforming in shape to the section of the wing. As shown, lugs b, d are disposed in the region FS of the front spar, and similar lugs, c, e with locking pins g and lever m are disposed in the region RS of the rear spar, lever m being operated by link connection u with lever k. Lever m is not apertured to co-operate with rod q. Link u may be supported intermediate its ends on an idler link v.