AD 57-13-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Revo, Incorporated | Colonial C-1 | Airworthiness Directives; Colonial Model C-1 Aircraft |
Unsafe Condition
Cracks in the weld areas of engine pylon side strut attaching fittings (P/N 3208-10) may originate across the edge, leading to structural failure.
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Required Actions
Inspect with 10-power glass the engine pylon side strut attaching fittings (P/N 3208-10) for cracks in the weld areas. Salvage fittings with edge cracks by grinding to a maximum depth of 1/16 inch if possible; replace fittings with cracks outside edge areas or exceeding salvage limits.
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Compliance Time
within next 10 hours of operation or July 15, 1957, whichever occurs first, and every 100 hours' operation thereafter
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Affected Aircraft
Revo, Incorporated Colonial C-1 aircraft, all serial numbers
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Federal Register Abstract
Engine Strut Fittings
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_57-13-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 57-13-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Colonial Model C-1 Aircraft Subject: Engine Strut Fittings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Revo, Incorporated Model: Colonial C-1 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 57-13-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 57-13-01 SUBJECT HEADING: Airworthiness Directives; Colonial Model C-1 Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 57-13-01 COLONIAL: Applies to All Model C-1 Aircraft. Compliance required within next 10 hours of operation or July 15, 1957, whichever occurs first unless already accomplished, and every 100 hours' operation thereafter. Inspect with 10-power glass the engine pylon side strut attaching fittings (P/N 3208-10) for cracks in the weld areas. (Inspection may be readily accomplished after removal of the fairing cuff, P/N 5400-33.) Fittings with cracks originating across the edge may be salvaged for use if the crack can be removed by grinding to a maximum depth of 1/16 inch measured in from the edge. Fittings with cracks located in areas other than the edge or in excess of the salvage limits must be replaced. (Colonial Service Bulletin No. 4 revision 1 dated May 22, 1957, covers this same subject.) FOOTER:
Document Text
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AD Final Rules - DRS_57-13-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 57-13-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Colonial Model C-1 Aircraft Subject: Engine Strut Fittings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Revo, Incorporated Model: Colonial C-1 Product Type: Aircraft Product Subtype: Small 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: 57-13-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 57-13-01 SUBJECT HEADING: Airworthiness Directives; Colonial Model C-1 Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 57-13-01 COLONIAL: Applies to All Model C-1 Aircraft. Compliance required within next 10 hours of operation or July 15, 1957, whichever occurs first unless already accomplished, and every 100 hours' operation thereafter. Inspect with 10-power glass the engine pylon side strut attaching fittings (P/N 3208-10) for cracks in the weld areas. (Inspection may be readily accomplished after removal of the fairing cuff, P/N 5400-33.) Fittings with cracks originating across the edge may be salvaged for use if the crack can be removed by grinding to a maximum depth of 1/16 inch measured in from the edge. Fittings with cracks located in areas other than the edge or in excess of the salvage limits must be replaced. (Colonial Service Bulletin No. 4 revision 1 dated May 22, 1957, covers this same subject.) FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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