N395DC
Registered owner: CBG LLC, OR (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
3 reports on file, 2016-10-02 – 2025-05-17.
Part: CHECK VALVE — FAULTED (NR 1 ENGINE) · airframe 18,481 hrs · 19,365 cycles
E1 POPPING/BANGING DURING POWER REDUCTION FOR LANDING. ENGINE OIL PRESSURE FLUCTUATING NO RWP LIGHT OR TEMP CHANGE. REPLACED CHECK VALVE ON E1 BLEED AIR LINE FOR HIGH PRESSURE LINE. IAW PW306B MM 75-00-00 GROUND RUNS / OPS CHECK GOOD.
Part: TIRE — FAILED (NR 3 MLG) · airframe 18,215 hrs · 19,056 cycles
#3 TIRE SEPARATION ON TAKEOFF. REMOVED & REPLACED #3 & #4 MLG WHEEL ASSY IAW DO328-300 TC 32.916
Part: COMPRESSOR — FATIGUED (NR 2 ENGINE) · airframe 11,635 hrs · 11,529 cycles
FLIGHT CREW REPORTED 2 LOUD BANGS OUT OF E2 WHILE LEVEL AT FL350. CHECKED ENGINE PAGE, ALL PARAMETERS NORMAL EXCEPT IPS FLUCTUATING BETWEEN .2 AND .5. NO FURTHER ANOMALIES. AIRCRAFT LANDED AT MX BASE WITH NO INCIDENT. MX PERSONNEL CONDUCTED BORESCOPE INSPECTION OF ENGINE AND FOUND SUBSTANTIAL DAMAGE TO THE NR 4 HP COMPRESSOR AND FOD DAMAGE FROM THE FAILED COMPRESSOR TO THE CENTRIFUGAL IMPELLER. ENGINE REMOVED AND SENT TO OVERHAUL FACILITY. DISASSEMBLED ENGINE AND FOUND THE NR 4 COMPRESSOR "EXHIBITED ONE FRACTURED BLADE." THE ROTOR WAS FORWARDED TO PWC MATERIAL LABORATORY FOR ADDITIONAL ANALYSIS. ENGINEERS CONDUCTED AN ANALYSIS OF THE FAILURE, INCLUDING SEM AND EDS INSPECTION, AND CONCLUDED THAT "THE 4TH STAGE ROTOR BLADE FRACTURED 0.12" ABOVE THE RIM AS A RESULT OF FATIGUE. THE FATIGUE CRACK INITIATED FROM MULTIPLE LOCATIONS ALONG THE PRESSURE SIDE OF THE AIRFOIL APPROXIMATELY 0.2" FROM THE LEADING EDGE. INITIALLY THE FATIGUE CRACK PROPAGATED TOWARDS THE AIRFOIL SUCTION SIDE AND TOWARDS TOE TRAILING EDGE UNTIL FINAL FRACTURE BY OVERLOAD. THE ROOT CAUSE OF THE FATIGUE INITIATION COULD NOT BE DETERMINED." THE PART HAD 1723 TOTAL CYCLES SINCE NEW ==, ROUGHLY 12% INTO ITS EXPECTED 15,000 CYCLE LIFESPAN.