Amdt. 39-349 Part 39 Federal Register February 11, 1967
Applies to Models 415C, 415CD, 415D, E, G, and F1 Series Airplanes, Serial Numbers 1 through 5714
inclusive, Except Those Airplanes Modified in Accordance with Either Ercoupe Service Memorandum No.
63 or Air Products Document No. 110.
Compliance required as indicated.
To prevent loss of rudder control, accomplish the following:
(a) Before further flight, after the effective date of this AD, with the nosegear raised off the ground,
inspect the rudder control system by checking the rudder controls from the cockpit for freedom of
movement through the entire range of rudder control travel. If any restriction or impediment on the
normal freedom of movement of the rudder controls is apparent, the cause thereof must be
determined prior to further flight. If it is determined that the restriction or impediment is caused by
binding in the rudder bellcrank at the stabilizer, before further flight, modify the rudder bellcrank
assembly in a manner prescribed in (c) of this AD.
(b) If the rudder bellcrank assembly is not modified as a result of findings made during the inspection
provided in (a), then it must be modified in a manner prescribed in (c) of this AD within fifty (50)
hours time in service after the effective date of this AD.
(c) Modify the rudder bellcrank assembly in accordance with any one of the following
(1) One of the two methods contained in Alon Service Bulletin No. 14, dated February 3, 1967; or
(2) The method contained in Ercoupe Service Memorandum No. 63 (available upon request from
Alon, Inc., Municipal Airport, McPherson, Kansas); or,
(3) Any other method approved as equivalent by the Chief, Engineering and Manufacturing Branch,
Federal Aviation Agency, Central Region.
This directive effective February 11, 1967.