N430CM
Registered owner: SAN JUAN AVIATION LLC, DE (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) | Operator | 2010-08-04 – 2010-08-04 | Operator named in NTSB report |
| Chevron USA Inc | Operator | 2010-08-04 – 2010-08-04 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
WHILE IN A HOVER, DURING A TRACK AND BALANCE FLIGHT THE NR 1 HYD SYSTEM FAILED. INDICATED BY A MASTER CAUTION LIGHT AND LOSS OF NR 1 SYSTEM HYD PSI AND THE PEDALS GOT STIFF. PERFORMED LANDING AND CHECKED HYD PSI AND SHUT THE NR 1 SYSTEM OFF IAW THE EMERGENCY CHECK LIST, AND SHUT THE ACFT DOWN. HYDRAULIC LINE FAILED.
BIRD STRIKE ABOVE LT WINDOW.
NR1 M/ECU LIGHT ILLUMINATED IN FLIGHT ALONG WITH ECU INDICATION ABOVE NR1 ENGINE INDICATOR. FADEC ON NR 1 ENGINE FAILED.
AFTER RESETTING THE NR 2 GENERATOR FOR 3 TIMES IT WAS DETERMINED THAT THE VOLTAGE REGULATOR WAS THE PROBLEM.
PIN DEBONDED.
WORN DUE TO SHEAR RESTRAINT BEING WORN
BEARINGS SCUFFING AND CRACKED
WORN ELASTAMER
NR 1 ENGINE NP2 RPM PICKUP MALFUNCTIONED/FAILED. INSTALLED SERVICABLE PART.
SHORTLY AFTER TAKING OFF FROM ST37 I EXPERIENCED A NR 2 ECU FAILURE TO THE HIGH SIDE. FOLLOWED THE EMERGENCY CHECKLIST BY GOING TO MANUAL CONTROL OF NR 2 ENGINE AND RETURNED TO BASE WITHOUT FURTHER INCIDENT. THE MECHANICS DETERMINED THAT THE NR 2 ENGINE TORQUE TRANSMITTER FAILED. NOT THE ECU. REPLACED THE TORQUE TRANSMITTER AND OPERATIONAL FLIGHT CHECKED OK.
TAILBOOM CRACK UNDER NR 2 HANGAR BEARING MOUNT. BEARING MOUNT PULLED LOOSE. FOUND DURING ROUTINE PHASE INSPECTION.
ONE ROW OF LEDS BURNED OUT / REPLACED LIGHT ASSY.
PIN DEBONDED/ REPLACED RESTRAINT.
PIN DEBONDED/ REPLACED RESTRAINT.
BATTERY IS WEAK. CHARGED BATTERY AND PERFORMED CAPACITY CHECK. FAILED 1ST CHECK (23 MINUTES). PERFORMED CONDITIONING CHARGE, RESTED AND PERFORMED 2ND CHECK. FAILED 2ND CHECK (30 MINUTES). WORK PERFORMED IAW MFG BATTERY MANUALS. REPLACED BATTERY.
TRIM TAB ON MAIN ROTOR BLADE IS CRACKED. REPLACED TRIM TAB.
STUD IS CRACKED WHERE THREADS ATTACHES TO FLANGE. REPLACED STUD ASSEMBLY.
CRACKED WHERE THREADED PORTION TRANSITIONS TO FLANGED PART. REPLACED PART.
4 DOWN STOP STUDS CRACKED
C/FL (CHIP DETECTOR FAILURE) LIGHTS INTERMITTENT.
CHIP DETECTOR CIRCUIT-SHORTED. DETECTOR CAUSES PLANETARY LIGHT TO STAY ILLUMINATED. REPLACED PART.
FOUND CIRCUIT BREAKER POPPED FOR EFIS UNIT. WOULD NOT RESET. REPLACED EFIS UNIT WITH NEW.
CAM FOLLOWER IS BROKEN. BEARINGS BECOME CORRODED AND THE OUTER RACE SEPARATES FROM THE INNER RACE. DAMAGE WAS FOUND ON THE LEADING EDGE OF ONE TAIL ROTOR BLADE ON THIS AIRCRAFT, THE PREVIOUS DAY. IT IS SUSPECTED THAT THE BEARING OUTER RACE BECAME DISCONNECTED AND STRUCK THE TAIL ROTOR BLADE. TAIL ROTOR BLADE WAS REMOVED FROM SERVICE DUE TO DAMAGE. REPLACED LOWER CAM FOLLOWER ON RT PASSENGER DOOR, AND UPPER CAM FOLLOWER ON L/H PASSENGER DOOR.
CORNER OF IMPELLER BLADE IS BROKEN OFF. BROKEN AREA MEARURES 1/4 X 1/2 INCH. BROKE IMPELLER PIECE WAS FOUND IN THE TURBINE. REMOVED ENGINE FROM AIRCRAFT AND REPLACED IMPELLER.
TRANSMISSION SUMP CHIP LITE WOULD NOT PULSE. CLEANED MOISTURE FROM SUMP CONNECTOR PLUG. AIRCRAFT GROUND RUN O.K.
TAIL ROTOR PITCH CONTROL LINKS ARE WORN. REPLACED TAIL ROTOR PITCH CONTROL LINKS.
ROTOR BRAKE CYLINDER WEAK AT TIMES. REPLACED ROTOR BRAKE CYLINDER.
TAILBOOM STROBE LENS IS CRACKED. REPLACED LENS.
TAILBOOM STOBE LENS IS CRACKED. THIS LENS HAD 10 (TEN) HOURS TOTAL TIME. REPLACED LENS.
SOLENOID IS DEFECTIVE. SNAP RING ON SHAFT UNDER THE SPRING DOES NOT STAY IN GROOVE. REPLACED SOLENOID.