SDR AU980813

Service difficulty report · Turbine

Difficulty date
February 28, 1998
Submitted
March 26, 2000
Operation
General aviation
Engine
Ge CF680C
Part
Turbine
Condition
Fod
Location
Rt Engine
Stage of operation
TO
How discovered
O
Nature of condition
W, X
Precautionary procedure
C, E, D

As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.

What was found

(AUS) RIGHT ENGINE COMPRESSOR AND TURBINE SEVERELY DAMAGED. ENGINE STRIP AND INSPECTION FOUND SEVERE FOD TO ALL COMPRESSOR AND TURBINE STAGES DUE TO A 1/4 INCH HEXAGONAL DRIVE NR 2 PHILLIPS BIT. FROM THE LOCATION OF THE DAMAGE, IT WAS DETERMINED THAT THE FOD ENTERED THE ENGINE GAS PATH THROUGH A BLEED DUCT OPENING WHEN THE THRUST REVERSERS WERE OPEN DURING A PREVIOUS MAINTENANCE VISIT. FOD. PERSONNEL/MAINTENANCE ERROR.