| AN 01-25CN-2 | PARAGRAPH 6 |
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The lock nut is tightened against the actuator, and the actuator and tube end are jointly drilled and cottered. The actuator is extended to 3 5/8 ± 1/32 inches (measured from the center of the hinge pin holes to the end of the actuator screw jack), to assure proper throw of the trim tab. The clevis end can be adjusted so that the distance between the hinge pin center on the actuator and clevis-and-bolt-hole center is approximately 23-25/32 inches. The rudder tab actuating arm fairing located on the right side of the rudder is removed, and the actuating arm assembly is installed. The rudder tab control, located at the left of the pilot's seat, is set at 0_. before the flexible shaft is attached to the rudder tab actuator. Final adjustment of the trim tab is attained by turning the clevis end of the actuating arm assembly as required to align the trim tab center line with the rudder center line. The lock nut is tightened against the clevis end, and the clevis end and tube end are jointly drilled and cotter pinned. 3. The aileron trim tabs are fixed pieces of metal attached to the inboard trailing edge of each aileron. These tabs must be adjusted while the airplane is on the ground. Merely bend them up or down as desired. (2) TO REMOVE THE ELEVATOR CONTROL JACK SHAFTS. (a) To remove the forward jackshaft, disconnect the push-pull tube from its arm and the four cables from the horns. Remove the eight bolts attaching the three bearing supports to the bulkhead and remove the shaft and bearing supports. Then the bearing sup. ports may be removed if desired by removing the nuts at the end of the shaft. (b) The rear jackshaft may be removed by disconnecting the cables and link and then removing the four bolts which attach the bearings to their supports. (3) TO REMOVE THE WING FLAP CONTROL MECHANISM -The flap actuating strut and bell crank may be removed through doors in the bottom surface of the wing near the trailing edge, after the keel fairing has been removed. To remove a push pull tube it is necessary to separate the panels at the center line, remove the bolts which attach the turnbuckle fittings to the tube, and withdraw the tube in. board while sliding the fittings off the tube. |
(a) TO DISASSEMBLE THE HYDRAULIC FLAP ACTUATING CYLINDER.-When the wing panel is separated at the center bulkhead, the flap actuating cylinder may be easily removed for inspection and disassembly. First disconnect the two hydraulic lines at the cylinder. (See Figs. 93 and 94.) Next remove the two bolts attaching the bell crank arms to the piston shaft end "D". Remove the four bolts in the clamp assemblies which attach the cylinder to the center bulkhead. Place the cylinder "A" in wooden block clamps and insert in a vise. If block clamps are not available, use a vise with aluminum or copper covered jaws. With cylinder "A" held firmly, unscrew the end plug "C" using the spanner wrench (Drawing No. 87-88-030) which is carried in the tool compartment of the duffle bag. Pull the two cotter pins "H" and unscrew the nuts "G". Remove the washers "F" and pull bolts "E" which attach end "D" to the piston shaft "B". Remove piston assembly "B" from the cylinder through the uncapped end. The rubber piston cups "I" may now be inspected and replaced if necessary. Also inspect the rubber cup on the end plug "C" and the cup in the forward end of cylinder "A". If worn, replace with new cups. (b) TO ASSEMBLE THE HYDRAULIC FLAP ACTUATING CYLINDER. - Before assembling the cylinder, be sure that no dirt or foreign matter of any kind is on the parts to be assembled. To assemble, reverse the procedure outlined above. c. HYDRAULICS (Drawing No. 87-33-902). (1) GENERAL.
(a) HYDRAULIC SYSTEM. (See Fig. 95.)br> I. The hydraulic controls consist of an electrically-driven hydraulic pump for operating the retractable landing gear, tail wheel, and wing flaps, one hand pump for auxiliary operation, a toggle switch, mounted just below the grip on the control stick for operating the electric pump, a reserve tank assembly, aft of the fuselage access door on the left side of the fuselage, for hydraulic fluid, and a hydraulic control valve. The valve is equipped with two handles, on the left side of the cockpit. The tubing material in the hydraulic controls is "Everdur" or stainless steel tubing (Spec. 57-180-3) throughout except vent and drain lines which are aluminum alloy. |
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