- Effective
- August 25, 1965
- Published
- August 25, 1965
- Model
- 18A
- Data sheet
- TCDS1H17
- Registered aircraft
- 6 matched by model
- Product
- Aircraft · Rotorcraft
- Amendment
- 39-122
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 | a2311bb1…5b96449 | FAA DRS (API key needed) |
On this page
The airworthiness directive
65-19-01 AIR and SPACE: Amdt. 39-122 Part 39 Federal Register August 25, 1965. Applies to Model 18A Gyroplanes, Serial Numbers 18-7 through 18-28.
Compliance required before further flight unless already accomplished.
To prevent further failures of main rotor blade retention bolts while supporting the blade near the tip to prevent contact with the droop stops, replace three main rotor blade retention bolts, P/N RO-U18-2136-11, and nuts, P/N MS-20364-1614, with new main rotor blade retention bolts and nuts furnished by the manufacturer after August 4, 1965, and torque the nuts to 45 - 50 foot pounds dry thread torque value.
This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated August 10, 1965.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 6
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.