N139CN
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| CHEVRON USA PRODUCTION COMPANY (AC2A) | Certificate holder | — | Matched by certificate designator |
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.
7 reports on file, 2016-05-09 – 2019-12-04.
Part: BEARING — CRACKED (TAIL ROTOR) · airframe 8,620 hrs
THE BEARING P/N: 3T6510V00255 S/N: 16144 WAS INSTALLED NEW INTO BEARING SUPPORT P/N: 3T6510A00443 S/N: THB9999 AT 3565.2 HRS. THE BEARING SUPPORT WAS INSTALLED ONTO N139CN AT 8141.6 HRS AND WAS REMOVED FROM THE AIRCRAFT AT 8620.0 HRS DUE TO HIGH VIBRATION RECOGNIZED BY VXP. WHEN THE BEARING SUPPORT WAS INDUCTED INTO THE SHOP THE BEARING RACE WAS CRACKED. THE BEARING ONLY HAD 478.8 HOURS SINCE INSTALL. THE BEARING WAS REMOVED FROM BEARING SUPPORT P/N: 3T6510A00443 S/N: THB9999 AT 4044.0 HRS.
Part: DECK PLATE — DELAMINATED (FUSELAGE) · airframe 8,142 hrs · 15,975 cycles
SEVERAL DELAMINATION'S OCCURRED THROUGHOUT DECK.
Part: LONGERON — CRACKED (BS 6034) · airframe 7,548 hrs · 15,225 cycles
RIGHT SIDE INTERNAL LONGERON CRACKED AS BS 6034 FROM LIGHTNING HOLE WEBBING
Part: ATTACH FITTING — CRACKED (TAILBOOM) · airframe 7,548 hrs · 15,225 cycles
RIGHT UPPER TAIL STRUCTURE ATTACH FITTING HAD A CRACK ABOVE THE LOCK FASTENER.
Part: LOCK NUT — DEFECTIVE (TAIL ROTOR) · airframe 6,395 hrs
THIS REPORT IS FOR A LOCKNUT WITH A LOOSE LINER. 6 TO 8 OF THE NUTS IN THIS BATCH HAD LINERS THAT BECAME LOOSE WHEN TORQUE WAS APPLIED. THESE NUTS ARE USED ON TAIL ROTOR DAMPER BRACKET ATTACHMENT. WE HAVE REMOVED THIS BATCH, LOT NR J000020289-0000 OF NUTS FROM SERVICE.
Part: RING — DAMAGED (MAIN ROTOR HEAD) · airframe 6,395 hrs
DURING REMOVAL OF THE MAIN ROTOR HEAD ASSY, FIVE PRESSURE BOLTS WERE NOTED OF HAVING A LOSS OF TORQUE PRIOR TO REMOVAL. AFTER REMOVAL OF THE MAIN ROTOR HEAD ASSY, AND FURTHER INSPECTION, DAMAGE WAS FOUND TO THE LOWER CONICAL RING AND TO THE LOWER CONICAL RING SEAT ON THE MAST. DAMAGE TO THE CONICAL RING SEAT MEASURED .680 IN X .172 IN AND THE DEEPEST PIT MEASURING 0.019 IN. (0.48MM)
Part: DAMPER — WEAK (MAIN ROTOR) · airframe 6,147 hrs
WEAK M/R DAMPER CAUSED ENGINE TORQUE MISCOMPARE. CAUSED BY VIBRATION.