- Effective
- November 14, 1961
- Models
- 74DM6, 74DM7
- Data sheet
- TCDSP-886
- Product
- Propeller
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 | a2733d8f…c23c552 | FAA DRS (API key needed) |
On this page
The airworthiness directive
60-11-08 SENSENICH: Amdt. 166 Part 507 Federal Register May 28, 1960. Applies to M74DM Propellers Installed On Lycoming O-320-B Series Engines Except Propellers With An "A" or "K" prefix to the Serial Number.
Compliance required within the next 100 hours of flight time or by August 1, 1960, whichever comes first, and at each periodic inspection thereafter.
As a result of three incidents of cracked hubs, the following shall be accomplished:
(a) Remove the propeller and visually inspect for cracks originating in the pilot bore. In case of doubt, any of the approved methods for aluminum alloy inspections should be used. If cracks are found, the propeller shall be retired immediately from service.
(b) If no cracks are found, polish out any scratches in the bore and break and polish any sharp edges at the front and rear chamfer of the pilot bore.
(c) When the propeller is reinstalled, torque retaining bolts to 300 inch-pounds.
(Sensenich Service Bulletin No. R-8-1 covers the same subject.)
Revised November 14, 1961.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.