Required inspections of the ailerons, aileron balance assembly, and aileron rigging for looseness or wear, and required repair or replacement of parts as necessary.
Requires installing inspection openings in the outer wing panels, inspecting the wing outer panel structural components for corrosion, and repairing any corroded component.
Inspecting the wing center section for evidence of corrosion through the installation of inspection openings and use use of a specified scope and light source.
Prevent failure of the fuel line fittings or the gascolator due to the current airplane design configuration. Such failure could result in a lack of fuel to the engine with consequent loss of control of the airplane.
Inspection and rework to detect the use of improper screws attaching the left and right rudder pedal shaft assemblies to the nose wheel steering tie rods.
To prevent loss of rudder control inspect the rudder control system and modify the rudder bellcrank assembly in a manner prescribed in this AD.
Instructions to preclude failure of brittle bolts and the danger of the nose wheel turning crosswise during landing on aircraft incorporating Electrol hose gear with aluminum scissors.
Fatigue failures have continued to occur in the rudder main rib where the control horn is attached after installation of reinforcement plates.
Frequent failures of the rear spar center section due to cracking of the upper flange.
Failures of the rudder horn attachments, attributed to improper ground handling technique rather than to unusual flight loads.
Replacing leaky fuel tank with one made of stainless steel or aluminum alloy before the next flight.
Inspection of control cables for continual fraying and failure in the control column assembly.
To eliminate instances of the nose ski coming off when operating on Federal Aircraft Works Model A-1500 skis, a supplementary safety device should be installed.
Preventing elevator flutter in the event the elevator trim tab control wire fails by installing elevator trim tab stop and spring.
Listed airplanes may contain a control column shaft, P/N 415-52129, which is defective at its lower bearing fitting.
Checking the operation of the voltage regulator by observing the ammeter reading.
Install a new battery box drain tube to extend at least 1/2 inch below the fuselage belly skin if this has not been already incorporated in the airplane.
Flexing of the lower aileron skin has resulted in fatigue cracks in the beam in the balance weight area.
Cracks have occurred in the belly skin at the rearmost rivet attaching the center section belly skin outer stiffeners to the belly skin.
A positive locking device must be installed on the zipper in the baggage compartment bottom to prevent articles to fall through and foul the controls.