62-27-03 CURTISS-WRIGHT: Amdt. 525 Part 507 Federal Register December 28, 1962. Applies to all C-46 Series aircraft which have rudder assemblies P/N 20-140-5110 installed.
Compliance required as indicated.
A recent inflight failure of the rudder spring tab rod terminal resulted in the free flutter of the rudder spring tab which forced the rudder to oscillate. To preclude the failure of this rod terminal and the resulting loss of control of the aircraft, the following shall be accomplished:
(a) (1) Aircraft with less than 10,000 hours' time in service shall be inspected in accordance with (b) prior to the accumulation of 10,200 hours' time in service and thereafter every 400 hours' time in service.
(2) Aircraft with 10,000 or more hours' time in service shall be inspected in accordance with (b) within 200 hours' time in service after the effective date of this AD, unless already accomplished within the last 200 hours' time in service, and thereafter every 400hours' time in service from the last inspection.
(b) (1) Remove the clevis, P/N 20-530-5133-2, and AN 316-5R nut from the rudder spring tab rod assembly, P/N 20-530-5134-1.
(2) Inspect for cracks in the shoulder and threaded shank of the rod terminal, P/N 20-530-5132-2, using a dye penetrant, magnetic particle, or an FAA approved equivalent inspection method in conjunction with at least a 5-power magnifying glass.
(3) Replace cracked rod terminals, P/N 20-530-5132-2, prior to further flight.
(c) Rod terminals, P/N 20-530-5132-2, or rod assembly, P/N 20-530-5134-1, having zero or a known time in service not exceeding 5,000 hours, may be installed in compliance with (b)(3). Such parts shall be inspected and replaced in accordance with the following:
(1) Parts having less than 4,800 hours' time in service shall be inspected in accordance with paragraphs (b)(1) and (2) prior to the accumulation of 5,000 hours and thereafter every 400 hours' time in service.(2) Parts having 4,800 or more hours' time in service shall be inspected in accordance with paragraphs (b)(1) and (2) within the next 200 hours' time in service and thereafter every 400 hours' time in service.
(3) Cracked parts shall be replaced prior to further flight.
(d) The inspection required by paragraph (b) is no longer required when rod assembly, P/N 20530-5134-1, is replaced with a new Component Air, Inc., rod assembly, P/N CAI-46003-1, or with an FAA approved rod terminal and clevis, or a rod assembly incorporating a clevis with 3/8-24 UNF or 7/16-20 UNF threads.
(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.
This directive effective January 29, 1963.