AD 73-11-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-34-200 | Airworthiness Directives; Piper Model PA-34-200 Airplanes |
Unsafe Condition
Weakening of the main landing gear support structure due to cracks and/or wrinkles in wing ribs and skins, which may propagate from the forward lower corner of the rib web toward the aft upper corner, and cracks at the main landing gear aft trunnion fitting attachment point.
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Required Actions
Visually check left and right wing lower surface skins for wrinkles outboard of the wheel well openings. If wrinkles are present, check wing ribs at wing station 69.24 for cracks/ wrinkles in the web. If wrinkles are present and modification kit 760 696V is not installed, check the aft false spar attachment area for cracks. Replace affected parts with serviceable parts or make an FAA-approved repair if cracks/ wrinkles are found. Repeat inspections every 10 hours time in service. After hard landings, perform the checks again. If modification kit 760 696V is installed and Service Bulletin 406 is complied with, repetitive inspections are no longer required.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours time in service from the last inspection
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Affected Aircraft
Piper Model PA-34-200 airplanes with serial numbers 34-E4 and 34-7250001 through 34-7450039
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Federal Register Abstract
Main Landing Gear Support Structure
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_73-11-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 73-11-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-34-200 Airplanes Subject: Main Landing Gear Support Structure Status: Current Citation: This information is not available. Citation Publish Date: 12/04/1973 Effective Date: 12/03/1973 Make: Piper Aircraft Inc. Model: PA-34-200 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 73-11-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1747 AD NUMBER: 73-11-02 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-34-200 Airplanes ACTION: SUMMARY: DATES: Effective December 3, 1973. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 73-11-02 PIPER: Amdt. 39-1639 as amended by Amendment 39-1649 is further amended by Amendment 39-1747. Applies to Model PA-34-200 airplanes Serial Numbers 34-E4 and 34-7250001 through 34-7450039 certificated in all categories. Compliance required within the next 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours time in service from the last inspection. To detect weakening of the main landing gear support structure, accomplish the following: (a) Visually check both left and right wing lower surface skins for wrinkling immediately outboard of the wheel well openings. (b) If wrinkles are present, visually check the wing ribs located at the outer end of the wheel wells (wing station 69.24) for cracks and/or wrinkles in the web. These cracks or wrinkles emanate from the forward lower corner where the rib attaches to the main spar and may propagate toward the aft upper corner of the web. (c) If wrinkles are present and Aft Wing Modification Kit, Piper Part No. 760 696V, has not been installed, check the area where the main landing gear aft trunnion fitting attaches to the aft false spar for cracks. (d) If cracks or wrinkles are present in the areas described in (b) or (c), replace affected parts with serviceable parts of the same part number or make an FAA approved repair before further flight. The checks required by paragraphs (a), (b) and (c) should also be accomplished after unusually fast and/or hard landings. Piper Service Bulletin No. 369 pertains to this subject. The initial inspection and repetitive inspections at 10 hours intervals are still required after compliance with Piper Service Bulletin No. 369, and/or after repair/replacement of the rib has been accomplished. The checks required by paragraph (a) may be performed by the pilot. When aft wing modification kit Piper Part No. 760 696V has been installed and the inspection and reservicing of the main landing gear oleo struts has been accomplished in accordance with the "Instructions" section of Piper Service Bulletin No. 406, the repetitive inspections in (a), (b), and (c) above are no longer necessary. NOTE: Serial Numbers 34-7250023; 34-7250090; 34-7250203; 34-7250262; 34- 7250275; 34-7250282; 34-7250290; 34-7250296; 34-7250316; 34-7250317; 34-7250319; 34- 7250322; 34-7250325; 34-7250326; 34-7250328; 34-7250330; 34-7250331; 34-7250333; 34- 7250334; and 34-7250336 and up have had Piper Kit No. 760696V installed at the factory. Amendment 39-1639 became effective May 21, 1973. Amendment 39-1649 became effective May 31, 1973. This Amendment 39-1747 becomes effective December 3, 1973. FOOTER:
Document Text
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AD Final Rules - DRS_73-11-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 73-11-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-34-200 Airplanes Subject: Main Landing Gear Support Structure Status: Current Citation: This information is not available. Citation Publish Date: 12/04/1973 Effective Date: 12/03/1973 Make: Piper Aircraft Inc. Model: PA-34-200 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 73-11-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1747 AD NUMBER: 73-11-02 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-34-200 Airplanes ACTION: SUMMARY: DATES: Effective December 3, 1973. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 73-11-02 PIPER: Amdt. 39-1639 as amended by Amendment 39-1649 is further amended by Amendment 39-1747. Applies to Model PA-34-200 airplanes Serial Numbers 34-E4 and 34-7250001 through 34-7450039 certificated in all categories. Compliance required within the next 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours time in service from the last inspection. To detect weakening of the main landing gear support structure, accomplish the following: (a) Visually check both left and right wing lower surface skins for wrinkling immediately outboard of the wheel well openings. (b) If wrinkles are present, visually check the wing ribs located at the outer end of the wheel wells (wing station 69.24) for cracks and/or wrinkles in the web. These cracks or wrinkles emanate from the forward lower corner where the rib attaches to the main spar and may propagate toward the aft upper corner of the web. (c) If wrinkles are present and Aft Wing Modification Kit, Piper Part No. 760 696V, has not been installed, check the area where the main landing gear aft trunnion fitting attaches to the aft false spar for cracks. (d) If cracks or wrinkles are present in the areas described in (b) or (c), replace affected parts with serviceable parts of the same part number or make an FAA approved repair before further flight. The checks required by paragraphs (a), (b) and (c) should also be accomplished after unusually fast and/or hard landings. Piper Service Bulletin No. 369 pertains to this subject. The initial inspection and repetitive inspections at 10 hours intervals are still required after compliance with Piper Service Bulletin No. 369, and/or after repair/replacement of the rib has been accomplished. The checks required by paragraph (a) may be performed by the pilot. When aft wing modification kit Piper Part No. 760 696V has been installed and the inspection and reservicing of the main landing gear oleo struts has been accomplished in accordance with the "Instructions" section of Piper Service Bulletin No. 406, the repetitive inspections in (a), (b), and (c) above are no longer necessary. NOTE: Serial Numbers 34-7250023; 34-7250090; 34-7250203; 34-7250262; 34- 7250275; 34-7250282; 34-7250290; 34-7250296; 34-7250316; 34-7250317; 34-7250319; 34- 7250322; 34-7250325; 34-7250326; 34-7250328; 34-7250330; 34-7250331; 34-7250333; 34- 7250334; and 34-7250336 and up have had Piper Kit No. 760696V installed at the factory. Amendment 39-1639 became effective May 21, 1973. Amendment 39-1649 became effective May 31, 1973. This Amendment 39-1747 becomes effective December 3, 1973. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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