- Models
- CF6-50A, CF6-50C, CF6-50C1, CF6-50C2, CF6-50C2B, CF6-50C2D and 5 more
- Data sheet
- TCDSE23EA
- Registered aircraft
- 20 matched by model
- Product
- Engine
- Amendment
- 39-3508
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 | e39b8489…0ba8367 | FAA DRS (API key needed) |
On this page
The airworthiness directive
79-13-09 GENERAL ELECTRIC: Amendment 39-3508. Applies to General Electric Model CF6-50 series engines containing stage 3-9 high pressure compressor rotor spools P/N 9081M49 (serial numbers as specified in the body of this AD) installed in, but not limited to certain McDonnell Douglas DC-10, Boeing 747, and Airbus Industries A-300 series aircraft certificated in all categories. Due to design differences, this AD does not affect CF6-6 series engines.
Compliance required within the next 30 calendar days after the effective date of this AD, unless previously accomplished.
To preclude possible engine failure resulting from compressor rotor spool fatigue cracking, remove from service stage 3-9 high pressure compressor rotor spools P/N 9081M49, Serial Numbers A0436, A0570, A0581, A0590, A0432 and A0443.
This amendment becomes effective upon publication in the Federal Register.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 20
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1973 | 2 |
|---|---|
| 1975 | 1 |
| 1976 | 1 |
| 1978 | 2 |
| 1979 | 1 |
| 1980 | 3 |
| 1985 | 1 |
| 1986 | 2 |
| 1988 | 4 |
| 2002 | 1 |
2 with no year recorded