66-30-04 FAIRCHILD-HILLER: Amendment 39-315 as amended by Amendment 39-493 and 39-711 is further amended by Amendment 39-2870. Applies to F-27 Type and FH-227 Type Airplanes, certificated in all categories.
Compliance required as indicated.
To detect cracks in the engine mount support tube assembly (post support) and engine mount support tube bracket (support assembly), accomplish the following:
(a) For airplanes equipped with upper tube assembly P/N 27-503105-11, -31, -41, -51; P/N 01-503105-11, or -31; upper bracket P/N 27-110105-11, -12, -31, -32, -41, -42, -51, -52, -61, -62, -71, -72, -81, or -82; or lower tube assembly P/N 27-503101-11, -41, -51, -61, -71, -81, -91, -101, or -111:
(1) Inspect in accordance with (c) the tube assemblies and brackets having 10,000 or more hours in service on the effective date of this A.D. within the next 50 hours in service after the effective date of this A.D. unless already accomplished within the last 250 hours in service, and thereafter at intervals not to exceed 300 hours in service from the last inspection.
(2) Inspect in accordance with (c) the tube assemblies and brackets having less than 10,000 hours in service on the effective date of this A.D. before the accumulation of 10,050 hours in service unless already accomplished after the accumulation of 9750 hours in service, and thereafter at intervals not to exceed 300 hours in service from the last inspection.
(b) Airplanes equipped with Fairchild Hiller brackets P/N 01-110105-3, -4, -11, -12, -13, -14, -31 or -32 must be inspected in accordance with (c) at intervals not to exceed 300 hours in service after the accumulation of 25000 hours in service.
(c) Without removing the tube assembly or bracket, clean all surfaces of each engine mount support tube bracket (four per airplane located at the wing front spar) and each engine mount support tube assembly (eight per airplane) prior to inspection. Visually inspect for cracks eachbracket and support tube assembly using a glass of at least 10 power or an FAA approved equivalent inspection. If cracks are found comply with (d) before further flight.
(d) Repair cracked parts in accordance with an FAA approved repair or replace them with a part of the same part number that has been inspected in accordance with (c) or with an FAA approved equivalent part. Equivalent repairs or parts may be installed when approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
(e) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
Fairchild Service Bulletins F27-54-14 and FH227-54-4, Revision 3 dated January 7, 1977, cover this subject.
Amendment 39-315 superseded AD 66-07-04.
Amendment 39-315 was effective December 10, 1966.
Amendment 39-493 was effective on October 21, 1967.
Amendment 39-711 was effective January 18, 1969.
This amendment 39-2870 is effective April 13, 1977.