AD 71-22-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | FH1100 Manufacturing Corporation | FH-1100 | Airworthiness Directives; Fairchild Hiller Model FH-1100 Helicopters |
Unsafe Condition
Failure of the FH1100 tail rotor bearing block, P/N 24-24010-3, due to cracks in the fuselage frame Station 163.5.
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Required Actions
Inspect fuselage frame Station 163.5 within the next 100 hours' time in service and every 100 hours thereafter per Service Bulletin FH1100-61-3. If cracks are found, alter the frame per the service bulletin's accomplishment instructions before further flight. If no cracks, accomplish alteration at next 1200-hour overhaul.
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Compliance Time
Within the next 100 hours' time in service, unless already accomplished, and every 100 hours after the last inspection. Incorporation of the alteration exempts from further compliance.
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Affected Aircraft
FH1100 Manufacturing Corporation Model FH-1100 helicopters, serial numbers 9 through 254.
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Federal Register Abstract
Tail Rotor Bearing Block
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_71-22-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 71-22-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Fairchild Hiller Model FH-1100 Helicopters Subject: Tail Rotor Bearing Block Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/20/1975 Make: FH1100 Manufacturing Corporation Model: FH-1100 Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 71-22-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2206 AD NUMBER: 71-22-03 SUBJECT HEADING: Airworthiness Directives; Fairchild Hiller Model FH-1100 Helicopters ACTION: SUMMARY: DATES: Effective May 20, 1975. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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 in accordance 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. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_71-22-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 71-22-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Fairchild Hiller Model FH-1100 Helicopters Subject: Tail Rotor Bearing Block Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/20/1975 Make: FH1100 Manufacturing Corporation Model: FH-1100 Product Type: Aircraft Product Subtype: Rotorcraft Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 71-22-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2206 AD NUMBER: 71-22-03 SUBJECT HEADING: Airworthiness Directives; Fairchild Hiller Model FH-1100 Helicopters ACTION: SUMMARY: DATES: Effective May 20, 1975. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 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 in accordance 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. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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