AD 77-03-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | 19A | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
| aircraft | Textron Aviation Inc. | 23 | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
| aircraft | Textron Aviation Inc. | A23 | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
| aircraft | Textron Aviation Inc. | A23-19 | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
| aircraft | Textron Aviation Inc. | A23-24 | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
| aircraft | Textron Aviation Inc. | A23A | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
| aircraft | Textron Aviation Inc. | A24 | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
| aircraft | Textron Aviation Inc. | B19 | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
| aircraft | Textron Aviation Inc. | B23 | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
| aircraft | Textron Aviation Inc. | C23 | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
| aircraft | Textron Aviation Inc. | M19A | Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes |
Unsafe Condition
Collapse during landing or in-flight separation of the main landing gear due to cracks around the fore and aft retention bolt hole in the main landing gear housings (male part).
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the main landing gear housings using dye penetrant procedures for cracks around the fore and aft retention bolt holes. If no cracks are found, reinstall the housings without installing any bolt in the retention bolt holes. If cracks are found, replace the cracked housings with new Beech Part No. 169-810011-25 assemblies before further flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 150 hours' time in service after the effective date for aircraft on 100-hour, progressive, or approved aircraft inspection programs, or within 18 months after the effective date for aircraft on annual inspections.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
BEECH Models A23-19, 19A, M19A, B19 (Serial Numbers MB-1 through MB-536); Models 23, A23, A23A, B23, C23 (Serial Numbers M-2 through M-1392); and Models A23-24 and A24 (Serial Numbers MA-1 through MA-368)
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Landing Gear
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_77-03-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-03-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and ...Show more Subject: Main Landing Gear Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/14/1977 Make: Textron Aviation Inc. Model: 19A | 23 | A23 | A23-19 | A23-24 | A23A | A24 | B19 | B23 | C23 | M19A 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: 77-03-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2827 AD NUMBER: 77-03-05 SUBJECT HEADING: Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes ACTION: SUMMARY: DATES: Effective March 14, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 77-03-05 BEECH: Amendment 39-2827. Applies to Models A23-19, 19A, M19A and B19 (Serial Numbers MB-1 through MB-536); Models 23, A23, A23A, B23 and C23 (Serial Numbers M-2 through M-1392); and Models A23-24 and A24 (Serial Numbers MA-1 through MA-368) airplanes certificated in all categories. Compliance: Required as indicated unless already accomplished. To prevent possible collapse during landing or in-flight separation of the main landing gear, accomplish the following in accordance with Beech Service Instructions No. 0465-202, Rev. I or later FAA approved Revisions: A. Within the next 150 hours' time in service after the effective date of this AD for those aircraft on 100 hour (FAR 91.169(b)) inspections, progressive (FAR 91.171) inspections or approved aircraft inspection program (FAR 135.60) or within eighteen (18) months after the effective date of this AD for those aircraft on annual (FAR 91.169(a)) inspections: 1. Remove left and right main landing gear housing (male part) from wing strut adapter (female part). 2. Using dye penetrant procedures, inspect the main landing gear housings (male part), in the areas around the fore and aft retention bolt hole for cracks. 3. If no cracks are found as a result of the inspection required in paragraph A.2.: a. Reinstall the main gear housings in accordance with Beech Service Instruction 0465-202, Revision I or later FAA approved revisions. b. Do not install any bolt in the fore and aft retention bolt hole. 4. If cracks are found during inspection required in paragraph A.2. above, prior to further flight: a. Replace any cracked main gear housing with a new Beech Part No. 169-810011-25 housing assembly in accordance with Beech Service Instructions 0465-202, Revision I or later FAA approved revisions. b. Do not install any bolt in the fore and aft retention bolt hole. NOTE. Even through Beech Service Instruction 0465-202, Rev. I refers to P/N 169- 810011-21 housing, Beech will ship a P/N 169-810011-25 housing assembly. The P/N 169- 810011-25 assembly consists of two bushings installed in a P/N 169-810011-21 housing. B. Any equivalent means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective March 14, 1977. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_77-03-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-03-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and ...Show more Subject: Main Landing Gear Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/14/1977 Make: Textron Aviation Inc. Model: 19A | 23 | A23 | A23-19 | A23-24 | A23A | A24 | B19 | B23 | C23 | M19A 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: 77-03-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2827 AD NUMBER: 77-03-05 SUBJECT HEADING: Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24 and A24 Airplanes ACTION: SUMMARY: DATES: Effective March 14, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 77-03-05 BEECH: Amendment 39-2827. Applies to Models A23-19, 19A, M19A and B19 (Serial Numbers MB-1 through MB-536); Models 23, A23, A23A, B23 and C23 (Serial Numbers M-2 through M-1392); and Models A23-24 and A24 (Serial Numbers MA-1 through MA-368) airplanes certificated in all categories. Compliance: Required as indicated unless already accomplished. To prevent possible collapse during landing or in-flight separation of the main landing gear, accomplish the following in accordance with Beech Service Instructions No. 0465-202, Rev. I or later FAA approved Revisions: A. Within the next 150 hours' time in service after the effective date of this AD for those aircraft on 100 hour (FAR 91.169(b)) inspections, progressive (FAR 91.171) inspections or approved aircraft inspection program (FAR 135.60) or within eighteen (18) months after the effective date of this AD for those aircraft on annual (FAR 91.169(a)) inspections: 1. Remove left and right main landing gear housing (male part) from wing strut adapter (female part). 2. Using dye penetrant procedures, inspect the main landing gear housings (male part), in the areas around the fore and aft retention bolt hole for cracks. 3. If no cracks are found as a result of the inspection required in paragraph A.2.: a. Reinstall the main gear housings in accordance with Beech Service Instruction 0465-202, Revision I or later FAA approved revisions. b. Do not install any bolt in the fore and aft retention bolt hole. 4. If cracks are found during inspection required in paragraph A.2. above, prior to further flight: a. Replace any cracked main gear housing with a new Beech Part No. 169-810011-25 housing assembly in accordance with Beech Service Instructions 0465-202, Revision I or later FAA approved revisions. b. Do not install any bolt in the fore and aft retention bolt hole. NOTE. Even through Beech Service Instruction 0465-202, Rev. I refers to P/N 169- 810011-21 housing, Beech will ship a P/N 169-810011-25 housing assembly. The P/N 169- 810011-25 assembly consists of two bushings installed in a P/N 169-810011-21 housing. B. Any equivalent means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective March 14, 1977. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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