AD 51-08-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Swift Museum Foundation, Inc. | GC-1A | Airworthiness Directives; Temco Models GC-1A and GC-1B Aircraft |
| aircraft | Swift Museum Foundation, Inc. | GC-1B | Airworthiness Directives; Temco Models GC-1A and GC-1B Aircraft |
Unsafe Condition
Looseness in the horizontal stabilizer front spar attachment to the fuselage bulkhead due to deformation or elongation of the AN 3 bolt holes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the horizontal stabilizer front spar attachment for looseness by removing AN 3 bolts. Reinstall bolts with specified torque if no deformation; if deformation exists, ream holes to 1/4-inch diameter and replace AN 3 bolts with AN 4 bolts, nuts, and washers, torqued to 80-90 inch-pounds. Repeat inspection at each periodic or annual inspection if AN 3 bolts are retained.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
at next periodic inspection but not later than May 1, 1951
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Temco Models GC-1A and GC-1B Aircraft - All Serial Numbers.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Stabilizer Spar Attachment
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_51-08-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 51-08-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Temco Models GC-1A and GC-1B Aircraft Subject: Stabilizer Spar Attachment 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Swift Museum Foundation, Inc. Model: GC-1A | GC-1B Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 51-08-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 51-08-03 SUBJECT HEADING: Airworthiness Directives; Temco Models GC-1A and GC-1B Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 51-08-03 TEMCO: Applies to Models GC-1A and GC-1B Aircraft - All Serial Numbers. Compliance required at next periodic inspection but not later than May 1, 1951. Inspect the horizontal stabilizer front spar attachment to the fuselage bulkhead for looseness. First remove all fairing or interfering items. Support the horizontal stabilizers on the fuselage so that their position cannot change; remove the four AN 3 bolts which attach the front stabilizer spar to the fuselage bulkhead. If there is no deformation or elongation of these bolt holes and if the holes in the stabilizer spar and the fuselage bulkhead are in correct alinement the AN 3 bolts should be reinstalled, torquing them to 25-30 inch-pounds. If there is deformation or elongation of the attach bolt holes, a repair can be accomplished by reaming these 3/16-inch holes to 1/4-inch diameter with the stabilizers firmly blocked in the proper position with the fuselage. The AN 3 bolts, nuts, and washers are to be replaced with AN 4 bolts, nuts, and washers, and they should be torqued to 80-90 inch-pounds in reassembling the stabilizer front spar attachment. The empennage and fairing which were removed for this inspection and repair are then reassembled on the airplane. If the AN 3 attachment bolts are retained, this inspection should be repeated at each periodic or annual inspection. If the AN 4 attachment bolts are installed, only the normal inspections of this attachment need be made. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_51-08-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 51-08-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Temco Models GC-1A and GC-1B Aircraft Subject: Stabilizer Spar Attachment 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: 51-08-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 51-08-03 SUBJECT HEADING: Airworthiness Directives; Temco Models GC-1A and GC-1B Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 51-08-03 TEMCO: Applies to Models GC-1A and GC-1B Aircraft - All Serial Numbers. Compliance required at next periodic inspection but not later than May 1, 1951. Inspect the horizontal stabilizer front spar attachment to the fuselage bulkhead for looseness. First remove all fairing or interfering items. Support the horizontal stabilizers on the fuselage so that their position cannot change; remove the four AN 3 bolts which attach the front stabilizer spar to the fuselage bulkhead. If there is no deformation or elongation of these bolt holes and if the holes in the stabilizer spar and the fuselage bulkhead are in correct alinement the AN 3 bolts should be reinstalled, torquing them to 25-30 inch-pounds. If there is deformation or elongation of the attach bolt holes, a repair can be accomplished by reaming these 3/16-inch holes to 1/4-inch diameter with the stabilizers firmly blocked in the proper position with the fuselage. The AN 3 bolts, nuts, and washers are to be replaced with AN 4 bolts, nuts, and washers, and they should be torqued to 80-90 inch-pounds in reassembling the stabilizer front spar attachment. The empennage and fairing which were removed for this inspection and repair are then reassembled on the airplane. If the AN 3 attachment bolts are retained, this inspection should be repeated at each periodic or annual inspection. If the AN 4 attachment bolts are installed, only the normal inspections of this attachment need be made. 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.
46-33-02
final ruleAirworthiness 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.
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.