AN 01-25CN-2 | PARAGRAPH 6 |
1. The movement of the stick for full aileron control is 201/2' either side of the center line of the Airplane. The turnbuckles of the cables are accessible through the inboard trailing edge of the wing when the flaps are lowered. 2. The adjustments on the links are located above the upper wing skin at the aft end of the control torque shaft. 3. All cables requiring specified tension are tested for correct loading by a tensiometer. (See Fig. 15.) 4. The following tensions are specified:
(b) ELEVATOR CONTROL. 1. The stick is connected to the elevator control by a push-pull tube to a lever on the front jack. shaft at Station 5. Bell cranks on the jackshaft at Station 5 are connected by two pairs of cables to bell cranks on a rear jackshaft at Station 16. From here a single short push-pull link connects to the elevator horn. The cables are crossed between bell cranks. The cables are accessible through the rear fuselage inspection doors. (See Fig. 92.) 2. The stop for the elevator system is an adjustable cylinder and piston unit attached to the front of the control stick and leading forward and down to attach to the wing match angle. 3. The stops for the aileron system are bolts through the arms on the aft end of the torque shaft. (c) RUDDER AND TAIL WHEEL CONTROLS. 1. The rudder system consists of a cable runing aft from the rudder pedals, which passes around a reduction pulley mounted on an arm at Station S. Two cables attached to the reduction pulley by turnbuckles lead aft, one connecting to the rudder horn, and the other to the tail wheel horn. |
These turnbuckles are accessible for adjustment through the door in the left side of the fuselage. Turnbuckles are also located at the rudder pedal and adjustments may be made from the cockpit. A run-around cable runs from one pedal forward, around two pulleys to the opposite pedal. 2. Each tail wheel control cable passes throng a pair of guide pulleys at Station 13. Slack in the cable is avoided by the use of two coil tension spring attached to the lift tube at the center line of the fuselage and to the cable at Station 12. The cable also incorporates a compression spring to avoid transmitting taxiing shock to the rudder pedals. 3. The rudder pedal stops are small casting mounted on the fuselage-wing attachment angle, o both sides of the cockpit near the floor. The rudder pedal in the full forward position strikes the adjustable stop screw head. (d) FLAP CONTROLS.-The flap control system consists of a hydraulic actuating strut mounted on the airplane center line bulkhead inside the win near the trailing edge. The motion is transmitted through bell cranks to span wise push-pull tubes in the wing. Five links with turnbuckles connect each flap to the push-pull tubes. For adjustment purposes, the links and turnbuckles may be reached through the trailing edge of the wing when the flaps are lowered. (e) TRIM TAB CONTROLS. 1. The elevator and rudder trim tab control are mounted on the left side of the cockpit. Motion transmitted by a chain and sprocket drive to the gear box mounted just forward of the rear elevator jack shaft. From this box three flexible shafts, 2 for the elevator and 1 for the rudder, transmit motion to tab control actuator unit. Short tie rods connect the actuators to the tabs on the elevators. A longer ro enclosed in a fairing on the right side of the rudder controls the rudder tab. Control chain tension is adjustable by turnbuckles accessible through the baggage compartment door. 2. The rudder trim tab setting is made with the rudder in neutral flight position. The rudder pedals are maintained in the neutral position by clamping the two pedals to a straight metal bar. In the assembly of the trim tab actuating arm, 7/8 ± 1/32-inch is allowed between the end the actuator screw jack and the end of the tube. |