CTHIn ForceLegislation
AD/CF6/75 - High Pressure Turbine Rotor Stage 1 Disc
General Electric Turbine Engines - CF6 SGeneral Electric Turbine Engines - CF6 Series
Start here
Get a plain-English read of General Electric Turbine Engines - CF6 S
Turn the raw legal text into a practical explanation grounded in AD/CF6/75 - High Pressure Turbine Rotor Stage 1 Disc.
General Electric Turbine Engines - CF6 Series
| AD/CF6/75 | High Pressure Turbine Rotor Stage 1 Disc | 6/2009 |
|---|
| Applicability: | General Electric Co. (GE) CF6-80A, CF6-80A1, CF6-80A2, and CF6-80A3 turbofan engines with a high-pressure turbine rotor (HPTR) stage 1 disc, part number (P/N) 9367M45G06, installed.Note 1: These engines are installed on, but not limited to, Airbus A310 series and Boeing 767 series aeroplanes. |
|---|---|
| Requirement: | Remove HPTR stage 1 discs, P/N 9367M45G06, from service before exceeding the new, reduced life limit of 2,075 cycles-since-new.Note 2: FAA AD 2009-07-10 Amdt 39-15869 dated 25 March 2009 refers. |
| Compliance: | From the effective date of this AD, unless previously accomplished. |
| This Airworthiness Directive becomes effective on 4 June 2009. | |
| Background: | This AD results from an error by GE that incorrectly cited a cyclic life of 12,600 CSN in the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) for the HPTR stage 1 disc, P/N 9367M45G06. The issuing of this AD is to prevent the HPTR stage 1 disk from exceeding its part life, which could cause fatigue cracks to start and grow. These cracks could result in a possible uncontained disc failure and damage to the aeroplane. |
Image unavailable in extracted text
James Coyne
Delegate of the Civil Aviation Safety Authority
17 April 2009