67-12-04 FAIRCHILD-HILLER: Amdt. 39-391 Part 39 Federal Register April 8, 1967. Applies to Models F-27 Series and FH-227 Series Airplanes.
Compliance required as indicated.
To detect cracks in the rudder horn assembly, accomplish the following:
(a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 450 hours' time in service, and thereafter at intervals not to exceed 500 hours' time in service from the last inspection, comply with (b).
(b) Visually inspect the rudder horn assembly, P/N 27-243018-11, for cracks, using a glass of at least 10-power, or use an equivalent inspection approved by an FAA maintenance inspector. If a crack is found comply with (c) before further flight.
(c) Replace a cracked part with a part of the same part number that has been inspected in accordance with (b), or use an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
(d) The repetitive inspection required by (a) may be discontinued when a modification, approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region is incorporated.
(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the initial compliance time and the repetitive inspection interval specified in this AD if the request contains substantiating data to justify the increase for that operator.
This directive effective April 8, 1967.