| AD Number | 71-22-03 | Status | Active |
| Effective Date | May 20, 1975 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-2206 |
| Product Type | ["Aircraft"] | Product Subtype | ["Rotorcraft"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | FH1100 Manufacturing Corporation |
| Model(s) | FH-1100 |
71-22-03 FAIRCHILD-HILLER: Amendment 39-1325 as amended by Amendment 39-2206. Applies to FH1100 Helicopters certificated in all categories, S/N's 9 through 254.
Compliance required as follows:
To preclude the possibility of failure of the FH1100 tail rotor bearing block, P/N 24-24010-3, inspect the fuselage frame Station 163.5 within the next 100 hours' time in service, unless already accomplished, and every 100 hours after the last inspection in accordance with Fairchild Hiller Service Bulletin FH1100-61-3, Section 4, Inspection Procedure. If cracks are found in the frame, prior to further flight, alter the frame according to procedures in the service bulletin, section 2, Accomplishment Instructions, or later FAA-approved revision or alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA - Eastern Region.
If no cracks are found during the 100-hour inspections, accomplish the alteration at the time of the next 1200-hour aircraft overhaul inaccordance with section 2, Accomplishment Instructions, of the referenced service bulletin or later FAA-approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA - Eastern Region. Incorporation of the alteration exempts the aircraft from further compliance with this airworthiness directive.
Amendment 39-1325 was effective November 2, 1971.
This amendment 39-2206 is effective May 20, 1975.