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/CF6/11 High Pressure Turbine Rotor - Stage 2 Disc Forward Embossment Inner Diameter Fillet Radius
Applicability: CF6-50/-45 series engines.
3/89 TX
Requirement: Rework or inspect and rework stage 2 high pressure turbine rotor discs specified by FAA AD 89-01-02 Amendment 39-6082 in accordance with the requirements of paras (a) or (b), (c) and (d) of the AD.
Compliance: Forthwith. The cycle count is to commence on the effective date specified in the AD.
Background: The FAA AD incorporates a manufacturer's Service Bulletin which states that cracks have been found in a forward embossment inner diameter fillet and these could adversely affect engine durability. The probable cause is an undersized fillet radius which is increased by the rework specified in the AD.
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