- Models
- 108, 108-1
- Data sheet
- TCDSA-767
- Registered aircraft
- 600 matched by model
- Product
- Aircraft · Small 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 | 18 KB | 1b7ceb4b…b05c578 | FAA DRS (API key needed) |
On this page
The airworthiness directive
47-50-12 STINSON: Applies to Model 108 Series Serial Numbers 1 through 3500. Compliance required every 100 hours of operation. Inspection of the stabilizer leading edge attachment to the fuselage should be made for fatigue cracks, after each 100 hours of operation. If fatigue cracks are present, reinforcements to the stabilizer fitting should be added. Inspection may be discontinued after reinforcement is installed. (Stinson Service Bulletin No. 254 dated September 5, 1947, covers this same subject.)
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 600
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1943 | 1 |
|---|---|
| 1945 | 2 |
| 1946 | 274 |
| 1947 | 184 |
| 1948 | 4 |
| 1950 | 1 |
| 1955 | 1 |
| 1956 | 2 |
131 with no year recorded