71-24-06 FAIRCHILD HILLER ROTORCRAFT: Amdt. 39-1338. Applies to FH1100 Type Helicopters Certificated in all Categories.
Compliance required as indicated.
To preclude fatigue failure of the rear attachment lug on engine mount strut P/N 24-63110-1 accomplish the following:
a. Within the next 25 hours' time in service after the effective date of this AD unless already accomplished, inspect and replace if necessary, engine mount strut P/N 24-63110-1 in accordance with Section 2, subsection A.1. and A.2., Accomplishment Instructions, Fairchild Hiller Service Bulletin SB FH1100-71-2 dated 30 September 1971 or later FAA-approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
b. Within the next 100 hours' time in service after the effective date of this AD unless already accomplished, alter engine mount strut P/N 24-63110-1 in accordance with Section 2, subsection A.3. through A.8., Accomplishment Instructions, F/H Service Bulletin SB FH1100-71-2 dated 30 September 1971 or later FAA-approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
This amendment is effective November 26, 1971.