Federal Register of Legislation
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES
General Electric Turbine Engines - CF6 Series
AD/CF6/20 High Pressure Compressor Rotor Stages 11 to 14 Vane to Spool Rubs
Applicability: CF6-80A and CF6-80C2.
Requirement: Action in accordance with the Technical Requirements of FAA AD 91-15-25 Amendment 39-7090.
Note: GE Service Bulletins 72-459 Revision 2 and 72-130 Revision 2 refer.
11/91
Compliance: As specified in the Requirement Document with an effective date of 28 November 1991.
Background: The FAA AD is prompted by reports of HPCR stages 11-14 spool-shafts found in service with spool rub. This condition, if not corrected could result in uncontained engine failure.
We try to embed the page this law was scraped from. If the site blocks framing, you still get the link and a local excerpt.
Last checked with source on —
Checking whether the official page can be embedded…
Plain-English simplify of this law: a short summary, key points, and both sides of the argument. Generated on first view via Replicate, then cached. Vote on what helps your study.
No study brief is cached for this law yet. Sign up to generate a plain-English brief.
Sign up to generate