- Effective
- August 8, 1972
- Models
- CF6-6D, CF6-6D1
- Data sheet
- TCDSE23EA
- Registered aircraft
- 11 matched by model
- Product
- Engine
- Amendment
- 39-1495
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 | 5d535640…40a9f40 | FAA DRS (API key needed) |
On this page
The airworthiness directive
72-16-03 GENERAL ELECTRIC: Amendment 39-1495. Applies to Models CF6-6D and CF6-6D1 turbofan engines.
Compliance required as indicated.
To prevent cracking and possible failure of stage 2 high pressure turbine discs, unless already accomplished, remove from service stage 2 high pressure turbine discs Part No. 9687M40P03, P04, P05, or P06 prior to reaching a life limit of 2100 cycles.
For the purposes of this AD, the definition of cycles is that appearing in the CF6 Shop Manual GEK 9266 Section 72-00-00 Inspection page 301.
(General Electric Alert Service Bulletin CF6 72-320 pertains to this subject.)
This amendment is effective August 8, 1972.
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 |