AD 71-08-05

71-08-05 FAIRCHILD-HILLER: Amdt. 39-1183 as amended by Amendment 39-1204 is further amended by Amendment 39-1315. Applies to all FH-227 and F-27 airplanes certificated in all categories.

Compliance required as indicated.

To detect cracks in FH-227 and F-27 Main Landing Gear Drag Strut Assemblies P/N 2.00259.002 Issue 2 and Issue 3, having 5000 hours' time or more accomplish the following:

a) Within the next 100 hours after the effective date of this AD unless already accomplished within the past 1100 hours and thereafter at intervals not to exceed 1200 hours:

1) Inspect the end fittings of Drag Strut Assembly P/N 2.00259.002 Issue 2 and Issue 3 at the taper dowel holes using a penetrant flaw detection method in conjunction with a glass of at least 10 power or an equivalent method approved by the FAA.

2) Replace cracked parts before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement can beperformed.

3) 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. Equivalent inspections, and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

4) Report the results of the initial inspection findings required by this AD to the Chief, Engineering and Manufacturing Branch, FAA Eastern Region (reporting approved by the Bureau of the Budget under B.O.B. No. 04-R0174).

Amendment 39-1183 was effective April 16, 1971. Amendment 39-1204 was effective May 11, 1971. This Amendment 39-1315 is effective October 14, 1971.