57 Wings

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TTP

B1-L3

ATA 57

Beech 90 Series

B2-L1

Wings

The King Air wing assembly consists of the center section and two outboard wing panels. The center section and outboard wing assemblies are of semimonocoque box construction. Both center section spars are I-beam sections built up from aluminum extruded tee caps, webbing and stiffeners. Similar construction is used in the outboard wing spars, except a combination of aluminum extrusion and formed U-channel members comprise the main spar caps, while those of the rear spar are composed of formed aluminum angles and cap strips.


WING PANELS

The wing panel consists of three substructures: the I-beam spar, the leading edge assembly, and the main box assembly. The wing panel leading edge assembly and the main box assembly are joined to the main spar by continuous hinges. A subspar is installed at the forward portion of the leading edge with the small space forward of this subspar utilized to route wiring and plumbing. Between the subspar and the main spar, bladder fuel tanks are installed. Additional bladder tanks are installed in the box section. On aircraft through LJ-1087, each outboard wing panel is attached to the center section with four bolts in tension. Starting with aircraft LJ-1088, the lower forward spar contains a three-element spar cap with the wing bolt mounted transversely and in shear. The three other bolts are in tension. The upper spar cap ends are serrated at each of the attach points and soft aluminum washers are used to prevent any minor movement between the wing panels and the center section. The center section is attached to, and is an integral part of, the fuselage.




WING CENTER SECTION

The center section main and rear spars are parallel and are continuous from one outboard wing attach joint to the other outboard wing attach joint. A subspar, with an attached removable leading edge, is installed forward of the main spar between the fuselage and each nacelle. The area forward of the subspar, within the removable leading edge, is used to route engine controls, plumbing, wiring, etc. A subspar, forward of the rear spar, provides a tunnel for control cables and shafts and serves as a fuel wall for the center section fuel tank bladder from the root rib to the nacelle. Landing gear hinge-point  structural  supports  in  the  nacelles are made of machined alloy plate. Formed sheet- metal formers and stringers establish the nacelle fairing and cavity for a nacelle bladder fuel tank above and forward of the wheel well.

WING BOLT, NUT, AND SPAR CAP FITTINGS INSPECTION

 

Periodically, the wing bolts must be removed and the nut, bolt, and spar attachment fittings must be inspected by florescent-dye penetrant and visually. This inspection is a SIRM requirement.


Only personnel trained by the aircraft manufacutere are qualified to perform the eddy current, magnetic particle, and florescent penetrant procedures described in the SIRM.


All personnel performing any Fluorescent Liquid Penetrant Inspection or Eddy Current Test Procedure shall be a certified Level II or Level III technician in accordance with NAS-410.



PTP 

Beech 90 Series

B1

LOC

B2





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