AD 46-33-02
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
Cracks originating at the joggles in the flange outboard of the stabilizer attachment points on the upper bulkhead at fuselage Station 167 may form, potentially extending into the web of the bulkhead.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Install Globe P/N 11-213-1471-1 R & L stiffeners on the flange of the upper bulkhead at fuselage Station 167 with six rivets per stiffener. Stop drill any existing cracks and install a 0.040-inch 24ST alclad reinforcing plate on the web if the crack extends into it, using rivets spaced no more than 3/4 inches apart.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
prior to October 1, 1946
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Globe Models GC-1A and GC-1B Aircraft, serial numbers 3 to 174 inclusive.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Fuselage Bulkhead Flange Stiffener
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_46-33-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 46-33-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Globe Models GC-1A and GC-1B Aircraft Subject: Fuselage Bulkhead Flange Stiffener 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Swift Museum Foundation, Inc. Model: GC-1A | GC-1B Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 46-33-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 46-33-02 SUBJECT HEADING: Airworthiness Directives; Globe Models GC-1A and GC-1B Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 46-33-02 GLOBE: (Was Mandatory Note 2 of AD-766-5.) Applies to Models GC-1A, GC-1B Aircraft Serial Numbers 3 to 174 Inclusive. Compliance required prior to October 1, 1946. Install stiffeners, Globe P/N 11-213-1471-1 R & L, on the flange of the upper bulkhead at fuselage Station 167, with six rivets per stiffener, to prevent the formation of cracks originating at the joggles in the flange outboard of the stabilizer attachment points. Any crack should be stop drilled. If it extends into the web of the bulkhead an 0.040-inch 24ST alclad reinforcing plate extending to the flange should be installed on the web with rivets spaced not more than 3/4 inches apart. (Globe Customer Service Maintenance Bulletin No. 2 covers this same subject.) FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_46-33-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 46-33-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Globe Models GC-1A and GC-1B Aircraft Subject: Fuselage Bulkhead Flange Stiffener 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: 46-33-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 46-33-02 SUBJECT HEADING: Airworthiness Directives; Globe Models GC-1A and GC-1B Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 46-33-02 GLOBE: (Was Mandatory Note 2 of AD-766-5.) Applies to Models GC-1A, GC-1B Aircraft Serial Numbers 3 to 174 Inclusive. Compliance required prior to October 1, 1946. Install stiffeners, Globe P/N 11-213-1471-1 R & L, on the flange of the upper bulkhead at fuselage Station 167, with six rivets per stiffener, to prevent the formation of cracks originating at the joggles in the flange outboard of the stabilizer attachment points. Any crack should be stop drilled. If it extends into the web of the bulkhead an 0.040-inch 24ST alclad reinforcing plate extending to the flange should be installed on the web with rivets spaced not more than 3/4 inches apart. (Globe Customer Service Maintenance Bulletin No. 2 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.
Related Airworthiness Directives
47-25-07
final ruleAirworthiness Directives; Globe Models GC-1A and GC-1B Aircraft
Unsafe Condition: Installation of steel sleeve Continental P/N 25206 at the forward end of the engine's left oil gallery outlet port may prevent positive lubrication to the No. 6 cylinder connecting rod bearing.
47-06-04
final ruleAirworthiness Directives; Globe Models GC-1A and GC-1B Aircraft
Unsafe Condition: The AN 960-616 washers under the nuts at the attachment of the main landing gear retraction links to the shock struts may not properly retain the bushings in the retraction links.
46-23-04
final ruleAirworthiness Directives; Globe Models GC-1A and GC-1B Aircraft
Unsafe Condition: The rivet seam attaching the upper skin of the outer wing panels to the main spar has insufficient reinforcement due to an inadvertent error in manufacture, risking structural failure.
48-28-01
final ruleAirworthiness Directives; Temco GC-1A and GC-1B Aircraft
Unsafe Condition: Cracks are occurring in the last bulkhead (Station 185) of the fuselage at the bottom rudder hinge and stop fitting.