AD 48-28-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Swift Museum Foundation, Inc. | GC-1A | Airworthiness Directives; Temco GC-1A and GC-1B Aircraft |
| aircraft | Swift Museum Foundation, Inc. | GC-1B | Airworthiness 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.
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Required Actions
Inspect the fuselage bulkhead at each 20 hours operation until compliance with reinforcement. If cracks are found, drill No. 50 check holes at end of each crack and install a steel reinforcement fitting per TEMCO Drawing 11-213-5074.
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Compliance Time
not later than September 1, 1948
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Affected Aircraft
Temco GC-1A and GC-1B Aircraft, all serial numbers
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Federal Register Abstract
Fuselage Bulkhead Rework
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_48-28-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 48-28-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Temco GC-1A and GC-1B Aircraft Subject: Fuselage Bulkhead Rework 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Swift Museum Foundation, Inc. Model: GC-1A | GC-1B Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 48-28-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 48-28-01 SUBJECT HEADING: Airworthiness Directives; Temco GC-1A and GC-1B Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 48-28-01 TEMCO: Applies to All Models GC-1A and GC-1B Aircraft. I. Inspection required at each 20 hours operation until compliance with item II is made. Cracks are occurring in the last bulkhead (Station 185) of the fuselage at the bottom rudder hinge and stop fitting, and the bulkhead must be inspected for such cracks. If cracks are found, a repair must be made in accordance with item II. II. Compliance required not later than September 1, 1948. To preclude the possibility of a structural failure in the rear bulkhead of the fuselage, at the bottom rudder hinge and stop, a steel reinforcement must be made as follows: 1. If cracks are found in the bulkhead drill No. 50 (0.07 diameter) check holes at end of each crack. 2. Fabricate and install a steel reinforcement fitting as defined in TEMCO Drawing 11-213-5074. The Texas Engineering and Manufacturing Co., Inc., will furnish free of charge the steel reinforcement fitting described in item 2. (TEMCO Customer Service Maintenance Bulletin No. 26 covers this same subject.) FOOTER:
Document Text
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AD Final Rules - DRS_48-28-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 48-28-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Temco GC-1A and GC-1B Aircraft Subject: Fuselage Bulkhead Rework 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: 48-28-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 48-28-01 SUBJECT HEADING: Airworthiness Directives; Temco GC-1A and GC-1B Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 48-28-01 TEMCO: Applies to All Models GC-1A and GC-1B Aircraft. I. Inspection required at each 20 hours operation until compliance with item II is made. Cracks are occurring in the last bulkhead (Station 185) of the fuselage at the bottom rudder hinge and stop fitting, and the bulkhead must be inspected for such cracks. If cracks are found, a repair must be made in accordance with item II. II. Compliance required not later than September 1, 1948. To preclude the possibility of a structural failure in the rear bulkhead of the fuselage, at the bottom rudder hinge and stop, a steel reinforcement must be made as follows: 1. If cracks are found in the bulkhead drill No. 50 (0.07 diameter) check holes at end of each crack. 2. Fabricate and install a steel reinforcement fitting as defined in TEMCO Drawing 11-213-5074. The Texas Engineering and Manufacturing Co., Inc., will furnish free of charge the steel reinforcement fitting described in item 2. (TEMCO Customer Service Maintenance Bulletin No. 26 covers this same subject.) FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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