N139JP
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
Maintenance disclosures
HEATER WILL NOT BLOW HOT AIR, DURING TROUBLESHOOTING FOUND HIGHT PRESSURE CHECK VALVE FLAPPER HALVES BEING SEPARATED FROM CHECK VALVE BODY ON ONE SIDE.
HEATER WILL NOT BLOW HOT AIR; DURING TROUBLESHOOTING FOUND HEATER TEMPERATURE CONTROL VALVE (P/N 3G2140V00751) TO BE DAMAGED FROM HIGHT PRESSURE CHECK VALVE (P/N 3G2140V00651) FLAPPER HALVES BEING SEPARATED FROM CHECK VALVE AND LODGED IN HEATER TEMPERATURE CONTROL VALVE AND PUNCTURING THE VALVE BODY.
WHEN ADVANCING #1 ENGINE FROM IDLE TO FLIGHT POSITION, #1 ENGINE BEGAN TO "RUN AWAY" AND THE AIRCRAFT SPUN APPROXIMATELY 25-30 DEGREES ON THE PAD AND STARTED TO ROLL OVER. THE PIC WAS STILL ON THE ENGINE MODE KNOB, IMMEDIATELY RETARDED TO #1 ENGINE BACK TO IDLE STOPPING THE LEFT YAW, AND ARRESTED THE ROLL AND THE AIRCRAFT RETURN TO FLAT "AIRFRAME LEVEL
FLUID LEAKING FROM VENT HOLE ON PRESSURE SWITCH.
HYDRAULIC FLUID LEAKING FROM VENT HOLE.
HEAD OF BOLT BROKE OFF.
OIL COOLER FAN BEARING CONTAMINATED.
HIGH RESISTANCE WHEN CLOSED. REMOVED AND INSTALLED SERVICEABLE SWITCH.
SWITCH WAS SHORTED TO CASE AND CAUSED LANDING GEAR NOT TO EXTEND PROPERLY. REMOVED AND INSTALLED SERVICEABLE SWITCH.
THE NR 2 ENGINE FIREWALL HAS A 45MM CRACK AT BS 5700, WL 2670 AND BUTT LINE 780. WE ARE REQUESTING OPTIONS FOR AN REPAIR OF THE CRACKED AREA. THE NR 1 ENGINE FIREWALL HAS AN 78MM CRACK AT BS 5700 AND WL 2670. WE ARE REQUESTING OPTIONS FOR AN REPAIR OF THE CRACKED AREA.
RT UPPER SKIN CORRODED BS 3120 - 6700.
FOUND MAIN ROTOR TENSION LINK CRACKED DURING VISUAL INSPECTION. REPLACED TENSION LINK.
DURING ROUTINE 50 HR INSP, FOUND THE SUPPORT FITTING WHERE THE INTERMEDIATE GEARBOX ATTACHES TO THE TAILBOOM WAS CRACKED. REMAINING ACFT IN OUR FLEET WERE INSPECTED AND NO OTHER DESCREPANCIES WERE FOUND.
(AC2R) CRACKED FORE AND AFT ANGLE, PN 3P5333A19561, RT SIDE FUEL DRY BAY AREA.
TURNING DOWNWIND AFTER TAKEOFF, NR 2 SERVO LIGHT ILLUMINATED. FOLLOWED ESTABLISHED EMERGENCY PROCEDURE. PRESSURE SWITCH MALFUNCTIONED.
DURING TRANSITION FROM CLIMB TO CRUISE FLIGHT THE ACFT DEVELOPED A SEVERE VIBRATION. FOUND TAIL ROTOR DAMPER ROD END BROKEN. REPLACED TAIL ROTOR BLADE AND DAMPER.
IN CRUISE FLIGHT, AT 3500 MSL, THE MGB CHIP SUMP CAS MESSAGE CAME ON. FOLLOWED THE EMERGENCY PROCEDURE. THE CHIP BURNER WOULD NOT CLEAR THE CHIP. LANDED AT AIRPORT WITHOUT INCIDENT. FOUND 3 SMALL FLAKES ON RT LOWER CHIP PLUG. PERFORMED SERVICEABILITY CHECK AND FOUND SERVICEABLE.
WHILE IN FLIGHT, NR 2 SERVO CAS LIGHT ILLUMINATED. ON HYDRAULIC SYSTEM SYNOPTIC PAGE, THE NR 2 FWD, RT, LT AND T/R SERVOS ALL INDICATED JAMS. EMERGENCY CHECK LIST WAS FOLLOWED AND AIRCRAFT RETURNED TO BASE. CLEANED ELECTRICAL CONNECTOR ON SERVO BYPASS SWITCHES, INSPECTED HYDRAULIC SYSTEM COMPONENTS AND GROUND RUN. AIRCRAFT RETURNED TO SERVICE.
THREE (3) CRACKS FOUND IN FUSELAGE TO TAILBOOM ATTACH STRUCTURE ON FUSELAGE SIDE. (1 )CRACK IN THE RADIUS OF THE BULKHEAD AND (2) CRACKS RADIATING FROM HILOK FASTENERS ON OUTER STRUCTURE THAT ENCAPSULATES THE ATTACH FITTING IN THE UPPER LT ATTACH POINT.
TAIL ROTOR DAMPER CLAMP CRACKED, REPLACED CLAMP.
SEAL BREAKING DOWN, COMING APART AND LEAVING A GAP, REPLACED SEAL.