AD 72-23-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Sabreliner Corporation | NA-265-40 | Airworthiness Directives; NORTH AMERICAN ROCKWELL Model NA-265-40, NA-265-50, and NA-265-60 |
| aircraft | Sabreliner Corporation | NA-265-60 | Airworthiness Directives; NORTH AMERICAN ROCKWELL Model NA-265-40, NA-265-50, and NA-265-60 |
Unsafe Condition
Cracks, tool marks, nicks, scratches, rust, or other minor surface blemishes on the main landing gear outer strut cylinder and inner trunnion (cone shaped) surface could result in structural failure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect and rework the main landing gear outer strut cylinder and inner trunnion surface per North American Rockwell Service Bulletin No. 72-15 or equivalent FAA-approved procedure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 100 hours' time in service, but not later than 90 days after the effective date of this A.D., whichever occurs first, unless already accomplished within the last 2300 hours' time in service, and thereafter at intervals not to exceed 2400 hours' time in service or 2400 landings, whichever occurs first, from the last inspection.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Sabreliner Corporation Model NA-265-40, Serial Numbers 282-1 thru 282-97; Model NA-265-50, Serial Number 287-1; and Model NA-265-60, Serial Numbers 306-1 thru 306-63.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Gear Strut Cylinder
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_72-23-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 72-23-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; NORTH AMERICAN ROCKWELL Model NA-265-40, NA-265-50, and NA-265-60 Subject: Main Gear Strut Cylinder Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/11/1972 Make: Sabreliner Corporation Model: NA-265-40 | NA-265-60 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 72-23-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1553 AD NUMBER: 72-23-04 SUBJECT HEADING: Airworthiness Directives; NORTH AMERICAN ROCKWELL Model NA-265-40, NA-265-50, and NA-265-60 ACTION: SUMMARY: DATES: Effective November 11, 1972. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 72-23-04 NORTH AMERICAN ROCKWELL: Amdt. 39-1553. Applies to Sabreliner Model NA-265-40, Serial Numbers 282-1 thru 282-97; Model NA-265-50, Serial Number 287-1; and Model NA-265-60, Serial Numbers 306-1 thru 306-63. Compliance required within the next 100 hours' time in service, but not later than 90 days after the effective date of this A.D., whichever occurs first, unless already accomplished within the last 2300 hours' time in service, and thereafter at intervals not to exceed 2400 hours' time in service or 2400 landings, whichever occurs first, from the last inspection. To detect and remove cracks, tool marks, nicks, scratches, rust or other minor surface blemishes, inspect and rework the main landing gear outer strut cylinder and inner trunnion (cone shaped) surface in accordance with the inspection and rework provisions of North American Rockwell Sabreliner Service Bulletin No. 72-15 dated 30 October 1972 or later FAA-approved revision, or an equivalent procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective November 11, 1972. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_72-23-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 72-23-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; NORTH AMERICAN ROCKWELL Model NA-265-40, NA-265-50, and NA-265-60 Subject: Main Gear Strut Cylinder Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/11/1972 Make: Sabreliner Corporation Model: NA-265-40 | NA-265-60 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: 72-23-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1553 AD NUMBER: 72-23-04 SUBJECT HEADING: Airworthiness Directives; NORTH AMERICAN ROCKWELL Model NA-265-40, NA-265-50, and NA-265-60 ACTION: SUMMARY: DATES: Effective November 11, 1972. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 72-23-04 NORTH AMERICAN ROCKWELL: Amdt. 39-1553. Applies to Sabreliner Model NA-265-40, Serial Numbers 282-1 thru 282-97; Model NA-265-50, Serial Number 287-1; and Model NA-265-60, Serial Numbers 306-1 thru 306-63. Compliance required within the next 100 hours' time in service, but not later than 90 days after the effective date of this A.D., whichever occurs first, unless already accomplished within the last 2300 hours' time in service, and thereafter at intervals not to exceed 2400 hours' time in service or 2400 landings, whichever occurs first, from the last inspection. To detect and remove cracks, tool marks, nicks, scratches, rust or other minor surface blemishes, inspect and rework the main landing gear outer strut cylinder and inner trunnion (cone shaped) surface in accordance with the inspection and rework provisions of North American Rockwell Sabreliner Service Bulletin No. 72-15 dated 30 October 1972 or later FAA-approved revision, or an equivalent procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective November 11, 1972. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.