AN 01-25CN-2	PARAGRAPH 1
	SECTION IV
	MAJOR COMPONENT PARTS AND INSTALLATION

1. WINGS. (Drawings No. 87-000-1000 and 87-030-1000.)    a. DESCRIPTION.      (1) The wing is an internally braced, full cantilever, multi-cellular, stressed-skin type, built in two pieces. These are joined at the airplane center line by a series of horizontal bolts through match angles riveted to the skin, and through a bulkhead between the panels. (See Fig. 29 and 30.) The fuselage connection is made by means of two tee sections on the upper surface which fit against angles on either side of the fuselage through which a series of bolts complete the joint. Aluminum alloys 24SO and 24ST constitute the major materials used in the construction of this wing.      (2) The wing tips are detachable for replacement in the event of damage. These tips are attached to the wing by a series of flush-type screws on the surface.      (3) Wells are built into the underside of the wing for the wing fuel tanks and landing gear wheels. The joint where the two wing sections connect will serve as a skid in case of an emergency landing with the wheels retracted.      (4) The ailerons are built with Frise-type aero. dynamic balance and are also dynamically balknced. The right and left aileron trim tabs are of the fixed type, and must be adjusted on the ground. The ailerons are constructed of metal, including a stressed skin leading edge, and are fabric covered. Three mounting bearings are provided on each aileron.      (5) Hydraulically-operated, split trailing edge flaps extend from within a few inches of the airplane center line to the inboard ends of the ailerons on the under surface of the wings. They are attached to the wing by contintious hinges running the full length of each flap.    b REMOVAL AND DISASSEMBLY. (See Fig. 33 and 34)      (1) TO REMOVE THE COMPLETE WINGThe manufacturer recommends that a cradle such as that shown in (Fig. 31) be used for the support of the

airplane and for the support of the wing after separa. tion from the fuselage. If a cradle of this type is not available, then a padded chordwise support, at least five inches wide and curved to fit the underside of the wing, should be placed approximately eight feet, three inches outboard from the airplane center line under each panel.      (a) Drain the belly tank at the drain on the bottom of the tank and remove the tank from the air. plane.      (b) If an airplane cradle (Fig. 32) is to be employect to support the airplane, be sure the jack point studs (Drawing No. 87-03-531) are installed on the lower surface of each wing.      (c) Remove the two side sections of the engine cowl and attach the forward hoisting sling clevis ends to the lugs on the engine mount (Fig. 14). Be sure to install the nuts on the clevis bolts or the airplane may be dropped in mid-air if these bolts should slip out. Attach the tail hoisting sling to a bar passed through the lift tube in the rear of the fuselage. Be sure that two 100-pound weights are attached to the lift tube, one weight on either side of the fuselage. Hoist the airplane onto the cradle.      (d) Drain all the fuel tanks.        1. The drain cock for the fuselage tank is located on the bottom side of the fuselage aft of the trailing edge.        2. Drain cock for the wing tank is located under the'wing on the left panel approximately five inches from the center line.      (e) Remove the lower engine cowling.      (f) Disconnect and remove the sway braces.      (g) Remove the keel fairing.      (h) Remove the wing fillets and fillet bulkheads attached to the wing and fuselage.      (i) Remove the cowl shutters.by removing the cowl shutter support channel and the entire exit duct as one unit.

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