N139FW
Registered owner: CHEVRON USA INC, MS (owner ≠ operator)
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
THE NEW DESIGN SWASHPLATE BOOT P/N 3G6230L01851 SEPARATED AND TORE AFTER 13.3 HOURS OPERATING TIME. BOOT WAS REMOVED AND SPLIT BOOT P/N 3G6230A06231 WAS INSTALLED.
MAIN GEARBOX OIL COOLER FAN DRIVE SEAL LEAKING
MAIN GEARBOX OIL COOLER FAN WAS REMOVED AND REPLACED DUE TO MGB FAN QUILL SEAL LEAKING ALLOWING OIL TO MIGRATE TO FAN BEARINGS. SEE SDR AC2A2021101513901 FOR SDR ON SEAL.
CLAMPED ADAPTER P/N 3G6320A16551, S/N DAT197 AND ADAPTER CLAMPS P/N 3G6320A16651, S/N AVI 0406 WERE REMOVED FROM MGB 3G6320A00134, S/N V44 IN PREPARATION FOR SHIPMENT OF MGB IN FOR OVERHAUL. ADAPTER AND CLAMPS DISPLAY EVIDENCE OF SIGNIFICANT WEAR OF 0.010" ON MATTING SURFACES.
CLAMPED ADAPTER P/N 3G6320A16551, S/N DAT197 AND ADAPTER CLAMPS P/N 3G6320A16661, S/N AVI 0406 WERE REMOVED FROM MGB 3G6320A001434, S/N V44 IN PREPARATION FOR SHIPMENT OF MGB IN FOR OVERHAUL. ADAPTER AND CLAMPS DISPLAY EVIDENCE OF SIGNIFICANT WEAR OF 0.010" ON MATTING SURFACES.
OIL COOLER FAN WAS REMOVED AND REPLACED DUE TO MGB FAN QUILL SEAL LEAKING ALLOWING OIL TO MIGRATE TO FAN BEARINGS. TEARDOWN REPORT INDICATES BEARINGS WORN AND REPLACED WITH ONLY 284.4 HOURS SINCE OVERHAUL.
MAIN ROTOR BLADE TIP CAP ATTACHMENT BOND LINE SEPARATION.
OIL COOLER FAN WAS REMOVED AND REPLACED DUE TO MGB FAN QUILL SEAL LEAKING ALLOWING OIL TO MIGRATE TO FAN BEARINGS. TEARDOWN REPORT INDICATES BEARINGS WORN AND REPLACED WITH ONLY 13.7HOURS SINCE LAST OVERHAUL
MAIN ROTOR UPPER SWASHPLATE BOOT TORN, METAL RINGS LOOSE, NO ACCEPT/REJECT CRITERIA PROVIDED BY MANUFACTURER, NO DETAILED INSPECTION CRITERIA AVAILABLE.
OIL COOLER FAN WAS REMOVED AND REPLACED DUE TO MGB FAN QUILL SEAL LEAKING ALLOWING OIL TO MIGRATE TO FAN BEARINGS. TEARDOWN REPORT INDICATES BEARINGS WORN AND REPLACED WITH ONLY 464.1 HOURS SINCE OVERHAUL.
DURING DAILY INSPECTION, NOTICED RIGHT SIDE MAIN GEARBOX CHIP DETECTOR NOT FULLY ENGAGED. UPON INVESTIGATION, FOUND RETENTION RING FOR CHIP DETECTOR HAD BECOME UN-STAKED FROM CHIP DETECTOR BODY.
NR 1 SERVO CAS ILLUMINATED IN FLIGHT. COMPLIED WITH HYD SERVO MALFUNCTION EMERGENCY PROCEDURES AND RETURNED TO BASE. REPLACED 31 HYD SERVO SWITCH.
IN CRUISE FLIGHT, NR 1 SERVO CAUTION LIGHT CAME ON. CHECKED HYD SCHEMATIC PAGE WHICH SHOWED ALL NT 1 SYS SERVOS IN YELLOW, REFERENCED EMERGENCY PROCEDURES CHECKLIST FOR NR 1 SERVO CAUTION LIGHT. LOWERED LANDING GEAR AND RETURNED TO DEPARTURE. DEFECTIVE SWITCH. REPLACED SWITCH.
COWLING WAS FOUND BURNED DURING EXHAUST BRACKET REPLACEMENT. BURNED AREA WAS APPROXIMATELY (2) INCHES BY (3) INCHES. COWLING WAS REPAIRED AND RETURNED TO SERVICE. ALL OTHER AIRCRAFT IN FLEET WERE INSPECTED AND FOUND OK PHOTO OF COWLING HAS BEEN SENT TO FSDO.
NR 1 ENGINE INLET SCREEN HAS BROKEN WIRES.
CRACKS FOUND IN FITTING AT UPPER LT TAILBOOM ATTACHMENT POINT RADIATING FROM HI-LOCS.
DURING NORMAL PROCEDURES COPILOT WAS ASSISTING DEPARTING PASSENGERS AND LUGGAGE, HE NOTICED THE NR 1 EXHAUST STACK CRACKED AND FOLDED BACK. AFTER SHUTDOWN AND FURTHER INSPECTION FOUND THE STACK CRACKED ABOUT 12 INCHES ALONG THE LOWER WELD SEAM AND IB CRACK ABOUT 6 INCHES, A CRACK PERPENDICULAR TO THE SEAM ABOUT 6 INCHES AND FOLDED BACK.
NR 1 ENGINE TRIM WAS INOPERABLE AND ECL 1 CAS MESSAGE. FOUND LEVER PIN SHEARED/REPLACED POWER LEVER QUADRANT.