- Models
- 340, 440
- Data sheet
- TCDS6A6
- Registered aircraft
- 12 matched by model
- Product
- Aircraft · Large airplane
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.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| FAA DRS HTML | 20 KB | aa4fa12e…ee45b46 | FAA DRS (API key needed) |
On this page
The airworthiness directive
60-14-01 CONVAIR: Amdt. 177 Part 507 Federal Register July 1, 1960. Applies to All Models 340/440 Aircraft. Compliance required as indicated.
Fatigue failures have occurred in the threaded area (piston end) of the main landing gear actuating cylinder rod assembly, P/N 340-5150107. In at least two instances, complete failure of the rod end occurred allowing the main gear to free fall to the down position causing excessive load to be placed on the airframe. As a result, the following must be accomplished on rod assemblies with more than 5,000 hours' time in service.
Within the next 425 hours' time in service, and every 425 hours thereafter, conduct a visual inspection using at least a 10-power magnifying glass or equivalent for cracks in the threaded portion of the main landing gear actuating cylinder rod assembly, P/N 340-5150107. If cracks are found, the cylinder rod assembly must be replaced or reworked in accordance with Convair Service Engineering Report 340-12, 440-11 or equivalent prior to further flight. Reworked salvaged parts or reworked sound parts are not subject to the special inspections.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 12
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1953 | 3 |
|---|---|
| 1955 | 3 |
| 1956 | 4 |
| 1958 | 1 |
1 with no year recorded