AD 73-07-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | D & R Nevada LLC | 22M | Airworthiness Directives; GENERAL DYNAMICS Model 22M Series Airplanes |
Unsafe Condition
Crack in rudder boost actuator fitting P/N 30-15701-1
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Required Actions
Inspect the rudder boost actuator fitting P/N 30-15701-1 in accordance with General Dynamics 880M S.B. No. A27-47. If cracks are found, replace the defective fittings with an identical part.
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Compliance Time
Within the next 150 hours' time in service after the effective date of this A.D., unless already accomplished within the last 250 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection
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Affected Aircraft
General Dynamics Model 22M Series airplanes certificated in all categories
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Federal Register Abstract
Crack in Rudder Boost Actuator
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_73-07-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 73-07-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; GENERAL DYNAMICS Model 22M Series Airplanes Subject: Crack in Rudder Boost Actuator Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/29/1973 Make: D & R Nevada LLC Model: 22M Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 73-07-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1612 AD NUMBER: 73-07-03 SUBJECT HEADING: Airworthiness Directives; GENERAL DYNAMICS Model 22M Series Airplanes ACTION: SUMMARY: DATES: Effective March 29, 1973. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 73-07-03 GENERAL DYNAMICS: Amdt. 39-1612. Applies to Model 22M Series airplanes certificated in all categories. Compliance required as indicated. To detect cracks and prevent further failures of the actuator fitting, accomplish the following: (1) Within the next 150 hours' time in service after the effective date of this A.D., unless already accomplished within the last 250 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, inspect the rudder boost actuator fitting P/N 30-15701-1 in accordance with General Dynamics 880M S.B. No. A27-47 dated 1 March 1973, or later FAA-approved revision. (2) If, as a result of the inspection required by paragraph (1), cracks are found, replace the defective fittings with an identical part. This amendment becomes effective March 29, 1973. FOOTER:
Document Text
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AD Final Rules - DRS_73-07-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 73-07-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; GENERAL DYNAMICS Model 22M Series Airplanes Subject: Crack in Rudder Boost Actuator Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/29/1973 Make: D & R Nevada LLC Model: 22M Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 73-07-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1612 AD NUMBER: 73-07-03 SUBJECT HEADING: Airworthiness Directives; GENERAL DYNAMICS Model 22M Series Airplanes ACTION: SUMMARY: DATES: Effective March 29, 1973. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 73-07-03 GENERAL DYNAMICS: Amdt. 39-1612. Applies to Model 22M Series airplanes certificated in all categories. Compliance required as indicated. To detect cracks and prevent further failures of the actuator fitting, accomplish the following: (1) Within the next 150 hours' time in service after the effective date of this A.D., unless already accomplished within the last 250 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, inspect the rudder boost actuator fitting P/N 30-15701-1 in accordance with General Dynamics 880M S.B. No. A27-47 dated 1 March 1973, or later FAA-approved revision. (2) If, as a result of the inspection required by paragraph (1), cracks are found, replace the defective fittings with an identical part. This amendment becomes effective March 29, 1973. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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