AD 78-16-06
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | B19 | Airworthiness Directives; BEECH Models B19, C23, B24R, and C24R Airplanes |
| aircraft | Textron Aviation Inc. | B24R | Airworthiness Directives; BEECH Models B19, C23, B24R, and C24R Airplanes |
| aircraft | Textron Aviation Inc. | C23 | Airworthiness Directives; BEECH Models B19, C23, B24R, and C24R Airplanes |
| aircraft | Textron Aviation Inc. | C24R | Airworthiness Directives; BEECH Models B19, C23, B24R, and C24R Airplanes |
Unsafe Condition
Failure of the stabilator trim tab actuator rod due to improper rivet location, insecure rivets, or insecure clevis fittings could result in loss of trim tab control.
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Required Actions
Visually inspect both ends of the stabilator trim tab actuator rod for proper rivet location, rivet security, and clevis fitting security. Rework as necessary per Beechcraft Service Instructions Number 0994 or approved revisions. Equivalent methods require approval from the FAA's Engineering and Manufacturing Branch.
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Compliance Time
within the next 25 hours time-in-service after the effective date of this AD
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Affected Aircraft
BEECH Models B19 (MB-558 through MB-886), C23 (M-1413, M-1414, M-1416 through M-1418, M-1420 through M-1422, M-1424 through M-1438, M-1440 through M-1446, M-1448 through M-2009, M-1411 through M-2015, and M-2017 through M-2020), B24R (MC-151 through MC-448, MC-450, MC-451), and C24R (MC-449, MC-452 through MC-559, MC-561 through MC-563, MC-565 through MC-568 and MC-571)
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Structural Integrity of Trim Tab Rod
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_78-16-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 78-16-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BEECH Models B19, C23, B24R, and C24R Airplanes Subject: Structural Integrity of Trim Tab Rod Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/14/1978 Make: Textron Aviation Inc. Model: B19 | B24R | C23 | C24R 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: 78-16-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3275 AD NUMBER: 78-16-06 SUBJECT HEADING: Airworthiness Directives; BEECH Models B19, C23, B24R, and C24R Airplanes ACTION: SUMMARY: DATES: Effective August 14, 1978. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 78-16-06 BEECH: Amendment 39-3275. Applies to the following models and serial number airplanes certificated in all categories: Model Serial Numbers B19 MB-558 through MB-886 C23 M-1413, M-1414, M-1416 through M-1418, M-1420 through M-1422, M-1424 through M-1438, M-1440 through M-1446, M-1448 through M-2009, M-2011 through M-2015, and M-2017 through M-2020. B24R MC-151 through MC-448, MC-450, and MC-451. C24R MC-449, MC-452 through MC-559, MC-561 through MC-563, MC-565 through MC-568 and MC-571. COMPLIANCE: Required as indicated unless already accomplished. To assure continued structural integrity of the rod between the stabilator trim tab actuator and the trim tab, within the next 25 hours time-in-service after the effective date of this AD, accomplish the following: A) Visually inspect both ends of the stabilator trim tab actuator rod for proper rivet location, security of rivets and security of clevis fittings and rework if necessary, all in accordance with Beechcraft Service Instructions Number 0994 or later approved revisions. B) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective on August 14, 1978. FOOTER:
Document Text
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AD Final Rules - DRS_78-16-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 78-16-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BEECH Models B19, C23, B24R, and C24R Airplanes Subject: Structural Integrity of Trim Tab Rod Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/14/1978 Make: Textron Aviation Inc. Model: B19 | B24R | C23 | C24R 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: 78-16-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3275 AD NUMBER: 78-16-06 SUBJECT HEADING: Airworthiness Directives; BEECH Models B19, C23, B24R, and C24R Airplanes ACTION: SUMMARY: DATES: Effective August 14, 1978. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 78-16-06 BEECH: Amendment 39-3275. Applies to the following models and serial number airplanes certificated in all categories: Model Serial Numbers B19 MB-558 through MB-886 C23 M-1413, M-1414, M-1416 through M-1418, M-1420 through M-1422, M-1424 through M-1438, M-1440 through M-1446, M-1448 through M-2009, M-2011 through M-2015, and M-2017 through M-2020. B24R MC-151 through MC-448, MC-450, and MC-451. C24R MC-449, MC-452 through MC-559, MC-561 through MC-563, MC-565 through MC-568 and MC-571. COMPLIANCE: Required as indicated unless already accomplished. To assure continued structural integrity of the rod between the stabilator trim tab actuator and the trim tab, within the next 25 hours time-in-service after the effective date of this AD, accomplish the following: A) Visually inspect both ends of the stabilator trim tab actuator rod for proper rivet location, security of rivets and security of clevis fittings and rework if necessary, all in accordance with Beechcraft Service Instructions Number 0994 or later approved revisions. B) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective on August 14, 1978. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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