| AD Number | 77-03-05 | Status | Active |
| Effective Date | March 14, 1977 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-2827 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Textron Aviation Inc. |
| Model(s) | 19A 23 A23 A23-19 A23-24 A23A A24 B19 B23 C23 M19A |
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 gearhousing (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.