- Effective
- July 12, 1974
- Models
- CF6-6D, CF6-6D1
- Data sheet
- TCDSE23EA
- Registered aircraft
- 11 matched by model
- Product
- Engine
- Amendment
- 39-1894
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 | 7e6d4d51…9f6dae0 | FAA DRS (API key needed) |
On this page
The airworthiness directive
74-14-08 GENERAL ELECTRIC: Amendment 39-1894. Applies to Models CF6-6D, 6D1, and 6H Turbofan Engines.
Compliance required by September 30, 1974.
To prevent expulsion from the engine of fifth stage low pressure turbine blades, unless already accomplished, install improved blade retainer P/N 9083M19P07 per the instructions of General Electric Service Bulletin (CF6-6) 72-399 Revision 1 dated March 20, 1974, or subsequent FAA approved revision.
This amendment becomes effective July 12, 1974.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 11
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1971 | 1 |
|---|---|
| 1972 | 1 |
| 1993 | 1 |
| 1995 | 2 |
| 1998 | 4 |
| 1999 | 2 |