- Effective
- December 21, 1965
- Models
- 2150, 2150A
- Data sheet
- TCDS4A19
- Registered aircraft
- 109 matched by model
- Product
- Aircraft · Small airplane
- Amendment
- 39-171
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
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|---|---|---|---|
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On this page
The airworthiness directive
65-28-05 MORRISEY: Amdt. 39-171 Part 39 Federal Register December 21, 1965. Applies to Models 2150 and 2150A Airplanes.
Compliance required as indicated, unless already accomplished.
To detect cracking in the weldments of strut assemblies, P/N's MO-11000 and MO-11002, for both the right and left oleos of the main landing gear where the scissor assemblies are attached, accomplish the following:
(a) Within 25 hours' time in service after the effeactive date of this AD and at intervals not to exceed 25 hours' time in service from the last inspection, visually inspect for cracks the upper and lower scissors attachment fittings of the main landing gear until accomplishment of (c).
(b) If cracks are found, reinforce in accordance with (c) before further flight.
(c) Reinforce upper and lower scissors attachment fittings by the addition of 4130 steel plates at three locations described in Figure 1 or accomplish an equivalent repair approved by the Chief, Aircraft Engineering Division, FAA Western Region.
This directive effective December 21, 1965.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 109
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1958 | 1 |
|---|---|
| 1959 | 2 |
| 1961 | 11 |
| 1962 | 5 |
| 1974 | 1 |
| 1975 | 3 |
| 1976 | 6 |
| 1977 | 13 |
| 1978 | 15 |
| 1979 | 20 |
| 1980 | 4 |
| 1982 | 1 |
| 1985 | 1 |
26 with no year recorded