AD 47-06-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Swift Museum Foundation, Inc. | GC-1A | Airworthiness Directives; GLOBE Models GC-1A and GC-1B Aircraft. |
| aircraft | Swift Museum Foundation, Inc. | GC-1B | Airworthiness Directives; GLOBE Models GC-1A and GC-1B Aircraft. |
Unsafe Condition
The main landing gear retraction system may have improper adjustments in the side brace down stop position, down lock plunger clearance, limit switch plunger depression, and emergency extension cable turnbuckle settings, leading to potential gear malfunctions or failure during operation.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect main landing gear retraction system adjustments for side brace position, down lock plunger clearance, limit switch plunger depression, and emergency extension cable turnbuckle settings. Ensure adjustments meet specified tolerances as outlined in Globe Customer Service Maintenance Bulletin No. 7.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
prior to April 1, 1947, and upon each 100 hours operation thereafter
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Affected Aircraft
Swift Museum Foundation, Inc. Models GC-1A and GC-1B Aircraft
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Federal Register Abstract
Main Landing Gear Retraction System
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_47-06-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 47-06-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; GLOBE Models GC-1A and GC-1B Aircraft. Subject: Main Landing Gear Retraction System Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Swift Museum Foundation, Inc. Model: GC-1A | GC-1B Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 47-06-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 47-06-01 SUBJECT HEADING: Airworthiness Directives; GLOBE Models GC-1A and GC-1B Aircraft. ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 47-06-01 GLOBE: (Was Service Note 1 of AD 766-5.) Applies to Models GC-1A and GC-1B Aircraft. To be accomplished prior to April 1, 1947, and upon each 100 hours operation thereafter. Inspect main landing gear retraction system to determine that adjustments are as follows: (1) When the side brace is against the down stop the middle joint should be 1/8 inch to 1/4 inch above dead center (3/16 inch to 5/16 inch if measured from edges of links in accordance with Globe Customer Service Maintenance Bulletin No. 7). (2) When the side brace is against the down stop and the down lock plunger is fully extended, covering at least 1/2 of the adjustment screw head, the clearance between the plunger and the screw head should be from 0.001 inch to 0.005 inch. (3) When the side brace is against the down stop the limit switch plunger should be depressed approximately 1/32 inch beyond the cutoff point. (4) The turnbuckle in the emergency extension cable should be adjusted so that on manual extension of the gear both down locks operate before the handcrank has been wound to the full down position. After it has been determined that the turnbuckle adjustment is satisfactory in this respect it should be determined also that with the handcrank wound to the full up position the cable length is sufficient to permit the up limit switches to cut off. (Globe Customer Service Maintenance Bulletin No. 7 covers this same subject.) FOOTER:
Document Text
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AD Final Rules - DRS_47-06-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 47-06-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; GLOBE Models GC-1A and GC-1B Aircraft. Subject: Main Landing Gear Retraction System Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Swift Museum Foundation, Inc. Model: GC-1A | GC-1B 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: 47-06-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 47-06-01 SUBJECT HEADING: Airworthiness Directives; GLOBE Models GC-1A and GC-1B Aircraft. ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 47-06-01 GLOBE: (Was Service Note 1 of AD 766-5.) Applies to Models GC-1A and GC-1B Aircraft. To be accomplished prior to April 1, 1947, and upon each 100 hours operation thereafter. Inspect main landing gear retraction system to determine that adjustments are as follows: (1) When the side brace is against the down stop the middle joint should be 1/8 inch to 1/4 inch above dead center (3/16 inch to 5/16 inch if measured from edges of links in accordance with Globe Customer Service Maintenance Bulletin No. 7). (2) When the side brace is against the down stop and the down lock plunger is fully extended, covering at least 1/2 of the adjustment screw head, the clearance between the plunger and the screw head should be from 0.001 inch to 0.005 inch. (3) When the side brace is against the down stop the limit switch plunger should be depressed approximately 1/32 inch beyond the cutoff point. (4) The turnbuckle in the emergency extension cable should be adjusted so that on manual extension of the gear both down locks operate before the handcrank has been wound to the full down position. After it has been determined that the turnbuckle adjustment is satisfactory in this respect it should be determined also that with the handcrank wound to the full up position the cable length is sufficient to permit the up limit switches to cut off. (Globe Customer Service Maintenance Bulletin No. 7 covers this same subject.) 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.
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