| AN 01-25CN-2 | PARAGRAPH 1 | |
| SECTION IV | ||
| MAJOR COMPONENT PARTS AND INSTALLATION |
|
and the cap from each end bearing. The control arm slips out of the socket on the control drum in the panel. (c) TO REMOVE THE WING FLAPS:-Disconnect the flap position indicator linkage from the flap. This indicator is located in the left panel, inside the wing, near the leading edge of the flap. Remove all clevis bolts which connect the flap control turnbuckles to the fiap. Then withdraw the two con. tinuous hinge pins by pulling steadily on the hinge pin loops located near the spanwise center of the flap. (See Fig. 37.) c. TEST BEFORE ASSEMBLY:-When installing a new wing or when assembling the airplane the first time, it is advisable to have about 30 men lift the complete wing and turn it over about its leading edge and listen for loose foreign objects which might possibly be within the wing. Anything loose within the wing will demand immediate attention. d. INSTALLATION. (1) To Install the Complete Wing (See Fig. 35) Assembly of the wing to the fuselage is a reversal of the procedure listed in paragraph 1. b. of this section. Additional information is listed below: (a) Before assembling the wing to the fuselage it is advisable to lubricate the mating surfaces of the wing-fuselage fittings with grease, AN-G-3. (b) In lowering the fuselage onto the wing, care must be taken not to damage the lower edge of the firewall, hydraulic lines, and other installations either on the wing or in the fuselage. (c) Lower the forward end of the fuselage slightly in advance of the * rear of the fuselage so that that front fittings at the firewall may be engaged first, and align and insert the bolts. Then lower the fuse. lage until the remainder -of the holes are aligned. In. stall the proper size bolts with the heads outboard, working progressively from front to rear. Install the three bolts attaching the trailing edge of the wing to the fuselage (center). (d) Because of the design of the wing, there are do adjustments to be made for incidence, dihedral, wash-in, or wash-out. (e) Fill the hydraulic system. (f) Fill the brake system. |
(g) If the fuel gage has been loosened or removed, readjust it at the tank. (h) Drain out any condensate that may have accumulated in the air speed lines. (2) TO INSTALL THE AILERON-.-Raise the aileron until the ball bearings on the ends of the aileron are seated in the upper half of the split clamp fittings on the panel, and the center hinge on the panel drops into place through a slot in the aileron leading edge. At the same time, it is necessary to guide the ball end of the control arm, with the composition waxed bush. ing installed into the socket of the drum in the panel. Clamp and bolt the end hinges and bolt the center hinge through an access door in the lower aileron surface.
(3) TO INSTALL THE WING FLAPS:-Interlock the flap hinge and hold the flap in position while inserting the hinge pins. The loop ends of the hinge pin may be clamped in the chuck of a low r.p.m. portable electric drill. Lubricate the hinge pin with engine oil, grade 77, and use the rotating motion of the drill to aid in feeding the hinge pin through the hinges. (See Fig. 37.) Attack all clevis ends of the turnbuckles to the flap and adjust the turnbuckle barrels to seat the flap at the trailing edge evenly. Lock. wire all turnbuckle barrels. (4) TO ADJUST THE FLAP POSITION IN. DICATOR:-With the flaps fully extended, adjust the turnbuckle to make the position indicator read "45". Raise the flaps and check the position of the indicator. It should be flush with the wing surface. Readjust the turnbuckle if necessary to bring the top of the indicator Rush with the wing skin. 2. TAIL GROUP. a. DESCRIPTION. (1) STABILIZERS. -The horizontal and ver. tical stabilizers are aluminum alloy, multi-cellular construction, and metal covered. The horizontal stabilizer is made up as one piece and attached to the fuselage |
|||||||
