What was found
(CAN) ON INSPECTION, A STAGE 4 BLADE WAS FOUND TO HAVE A 0.080 INCH CRACK THROUGH THE DOVE TAIL AREA ON THE TRAILING EDGE SIDE. OUR FILE NR SQID 07-00588 (TC NR 20070216008)
- Difficulty date
- February 16, 2007
- Submitted
- May 1, 2007
- Operation
- General aviation
- Engine
- Ge CT581401
- System (JASC)
- 7230 · Turbine Engine Compressor Section
- Part
- Blade
- Part number
- 5009T34P01
- Condition
- Cracked
- Location
- Compressor
- Component
- Compressor · Ge
- Component part number
- 5006T25G06
- Stage of operation
- IN
- How discovered
- 9
- Nature of condition
- O
- Precautionary procedure
- K
As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.