AD 48-14-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | Army AT-11 | Airworthiness Directives; Beech Model AT-11 and C18S Airplanes |
| aircraft | Textron Aviation Inc. | C18S | Airworthiness Directives; Beech Model AT-11 and C18S Airplanes |
Unsafe Condition
Wear caused by chafing of the cabin heater control housing on the lower member of the center section main wing spar in the landing gear nacelle area.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the lower member of the center section main wing spar in the landing gear nacelle area for evidence of wear caused by chafing. Either use clamps to support the housing or cover the control housing with a 20-inch length of synthetic rubber hose.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
By next periodic inspection but not later than July 1, 1948.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Beech Model AT-11 and C18S airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Wing Center Section Spar
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_48-14-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 48-14-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Beech Model AT-11 and C18S Airplanes Subject: Wing Center Section Spar Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Textron Aviation Inc. Model: Army AT-11 | C18S Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 48-14-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 48-14-03 SUBJECT HEADING: Airworthiness Directives; Beech Model AT-11 and C18S Airplanes ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 48-14-03 BEECH: Applies to Models AT-11 and C18S. Compliance required by next periodic inspection but not later than July 1, 1948. Inspect the lower member of the center section main wing spar in the landing gear nacelle area for evidence of wear caused by chafing of the cabin heater control housing. To prevent chafing either use clamps to support housing or cover control housing with 20-inch length of synthetic rubber hose. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_48-14-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 48-14-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Beech Model AT-11 and C18S Airplanes Subject: Wing Center Section Spar Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Textron Aviation Inc. Model: Army AT-11 | C18S 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: 48-14-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 48-14-03 SUBJECT HEADING: Airworthiness Directives; Beech Model AT-11 and C18S Airplanes ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 48-14-03 BEECH: Applies to Models AT-11 and C18S. Compliance required by next periodic inspection but not later than July 1, 1948. Inspect the lower member of the center section main wing spar in the landing gear nacelle area for evidence of wear caused by chafing of the cabin heater control housing. To prevent chafing either use clamps to support housing or cover control housing with 20-inch length of synthetic rubber hose. 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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