- Model
- A
- Data sheet
- TCDSATC 556
- Registered aircraft
- 1 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 | 19 KB | da321ed5…c478611 | FAA DRS (API key needed) |
On this page
The airworthiness directive
46-06-05 STINSON: (Was Service Note 1 of AD-556-1.) Applies to All Model A Aircraft.
After each 100 hours of operation, make a visual inspection (using at least a 4-power magnifying glass) of the main spar lower fittings at the outer wing panel to inner wing panel connection for small fatigue cracks at the fish-mouth weld connecting the fittings to the chord tubes of the spar. These cracks are most likely to originate at the inboard corners of the fish- mouth weld on the outer panel fitting. If any cracks are found, repairs should be made before further operation of the aircraft. Proposed methods of repair should be submitted for engineering approval.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 1
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.