Service difficulty report · Blades

Difficulty date
December 4, 2006
Submitted
January 19, 2007
Operation
General aviation
Engine
Pwa PT6A114A
Part
Blades
Condition
Cracked
Location
Engine
Part time
8,000 hours
Stage of operation
IN
How discovered
V
Nature of condition
O
Precautionary procedure
K

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

What was found

(CAN) SEE REPORT ATTACHED CRACK INDICATIONS WERE FOUND ON THE CT BLADES AT OVERHAUL. CRACKS WERE FATIGUE RELATED ON ALL THE CT BLADES. HOWEVER, THE ATTACHED REPORT STATES THAT THE CT BLADES DID NOT FAIL IN CREEP AS DETAILED IN MFG SILS, DUE TO OVERTEMP OR EXCEEDING ENGINE LIMITATIONS. FAILURE APPEARS TO BE DUE TO FLAP MODE VIBRATIONS. PLEASE REFER TO ATTACHED ENGINEERING REPORT FOR DETAILS. (TC NR 20061204006)