AD 74-20-04
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | MD Helicopters, Inc. | 369 | Airworthiness Directives; Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM Helicopters |
| aircraft | MD Helicopters, Inc. | 369A | Airworthiness Directives; Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM Helicopters |
| aircraft | MD Helicopters, Inc. | 369H | Airworthiness Directives; Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM Helicopters |
| aircraft | MD Helicopters, Inc. | 369HE | Airworthiness Directives; Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM Helicopters |
| aircraft | MD Helicopters, Inc. | 369HM | Airworthiness Directives; Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM Helicopters |
| aircraft | MD Helicopters, Inc. | 369HS | Airworthiness Directives; Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM Helicopters |
Unsafe Condition
Cracks, gouges, nicks, and scratches in the main rotor blade trailing edge could result in blade failure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect main rotor blade trailing edge per Hughes Service Information Notice HN-73 or FAA-approved revisions. Remove blade from service if cracks are found. Replace or repair blade if gouges, nicks, or scratches are found, prior to further flight. Equivalent procedures may be approved by FAA.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 25 hours of helicopter operation after the effective date of this AD, unless already accomplished within the last 75 hours of helicopter operation, and thereafter at intervals not to exceed 100 hours of helicopter operation from the last inspection.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Hughes Model 369, 369A, 369H, 369HE, 369HS, and 369HM helicopters certificated in all categories.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Rotor Blade
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_74-20-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 74-20-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM Helicopters Subject: Main Rotor Blade Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/25/1974 Make: MD Helicopters, Inc. Model: 369 | 369A | 369H | 369HE | 369HM | 369HS 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: AIRWORTHINESS DIRECTIVES FINAL RULES: 74-20-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1968 AD NUMBER: 74-20-04 SUBJECT HEADING: Airworthiness Directives; Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM Helicopters ACTION: SUMMARY: DATES: Effective September 25, 1974. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 74-20-04 HUGHES HELICOPTERS: Amendment 39-1968. Applies to Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM helicopters certificated in all categories. Compliance required within the next 25 hours' of helicopter operation after the effective date of this AD, unless already accomplished within the last 75 hours' of helicopter operation, and thereafter at intervals not to exceed 100 hours' of helicopter operation from the last inspection. To detect cracks, gouges, nicks and scratches in the main rotor blade trailing edge, accomplish the following: (a) Inspect the main rotor blade trailing edge in accordance with Hughes Service Information Notice. No. HN-73, dated August 19, 1974, or later FAA-approved revisions. (1) If cracks are found remove blade from service prior to further flight. (2) If gouges, nicks and/or scratches are found replace or repair blade prior to further flight in accordance with Hughes Service Information Notice, No. HN-73. (b) Equivalent inspection and repair procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region upon submittal of adequate substantiating data. (c) Aircraft may be flown to a base for performance of the inspections required by this AD per FAR's 21.197 and 21.199. This amendment becomes effective September 25, 1974. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_74-20-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 74-20-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM Helicopters Subject: Main Rotor Blade Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/25/1974 Make: MD Helicopters, Inc. Model: 369 | 369A | 369H | 369HE | 369HM | 369HS 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: AIRWORTHINESS DIRECTIVES FINAL RULES: 74-20-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1968 AD NUMBER: 74-20-04 SUBJECT HEADING: Airworthiness Directives; Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM Helicopters ACTION: SUMMARY: DATES: Effective September 25, 1974. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 74-20-04 HUGHES HELICOPTERS: Amendment 39-1968. Applies to Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM helicopters certificated in all categories. Compliance required within the next 25 hours' of helicopter operation after the effective date of this AD, unless already accomplished within the last 75 hours' of helicopter operation, and thereafter at intervals not to exceed 100 hours' of helicopter operation from the last inspection. To detect cracks, gouges, nicks and scratches in the main rotor blade trailing edge, accomplish the following: (a) Inspect the main rotor blade trailing edge in accordance with Hughes Service Information Notice. No. HN-73, dated August 19, 1974, or later FAA-approved revisions. (1) If cracks are found remove blade from service prior to further flight. (2) If gouges, nicks and/or scratches are found replace or repair blade prior to further flight in accordance with Hughes Service Information Notice, No. HN-73. (b) Equivalent inspection and repair procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region upon submittal of adequate substantiating data. (c) Aircraft may be flown to a base for performance of the inspections required by this AD per FAR's 21.197 and 21.199. This amendment becomes effective September 25, 1974. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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