To reduce the amount of oil passing through the breather tube and exhausting on the under-side of the aircraft, Continental Motors Corporation has a newly designed engine fitting which extends further into the engine case.
In order to supply an alternate source of breather air to eliminate the possibility of pressurizing the engine case in the event that icing occurs at the breather tube end, a slot has been added to the lower portion of the breather tube.
A correction in the wiring on current models has been incorporated to completely eliminate the possibility of overheating the generator if the master switch is turned off in flight for a prolonged period of time.
Replace the four sheet metal screws attaching your aircraft identification plate on with rivets or blind rivets.
To ensure that the rubber strips on the top of the rear engine baffles remain in place, it is necessary to staple them in six places.
To keep foreign particles out of the wheel bearings on the main landing gear, perform the following steps to accomplish the inserting of a cork into each hollow main landing gear axle.
To preclude the possibility of skin cracking around the Camloc fasteners and reinforcement on the engine cowling doors, Alon recommends the following stiffener and reinforcement be added on each door.
Rework to eliminate the possibility of fuel overflow and in-flight siphoning.
To provide a vertical support which will function in conjunction with the F-40400-86 horizontal support angle, install A40712-1 support spring as shown.
Frequently check for leakage or seepage of the fuselage fuel tank, and check all plumbing connections for proper tightness and weld seams of the tank for possible cracks.
Inspect all control surface hinges for evidence of loose or working hinge pins at a frequency of not less than at time of each periodic.
The following rework is to be accomplished by not later than the next periodic inspection to eliminate the possibility of a fuel line vapor lock occurring.
To eliminate the possibilities of main gear tire wear due to misalignment, the following methods may be used for checking and correction.
The purpose of this bulletin is to eliminate the possibilities of a rudder bellcrank seizure caused by the bakelite bushing that has expanded due to moisture within the bushing.
It is recommended that within the next twenty-five hours the heat muff be removed and the welded areas around the stack junctions and at the cylinder attach flange be closely inspected.
In some instances, fuel has been observed flowing during flight from the vented fuel-filler caps. To preclude this condition, accomplish the following instructions.
To provide tail position light visibility for compliance with CAR 03. 538.
Certain combinations of atmospheric conditions, aircraft attitudes, fuel levels and/or normal flight maneuvers, may result in a condition where fuel starvation can occur.
Reports have been received indicating overheating of cylinder heads. To provide continuous indication of engine operating temperatures accomplish the following.
There have been field reports of severe corrosion in the outer wing panel structure of several aircraft. The most effective means of preventing corrosion damage is early identification and correction.