N416PA
Registered owner: SKYWEST LEASING INC, UT (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| Transpac Aviation Academy | Operator | on 2016-05-12 | Operator named in NTSB report |
| PAN AM INTERNATIONAL FLIGHT ACADEMY | Operator | on 2008-03-15 | Operator named in NTSB report |
Accident & incident history
Operated by Transpac Aviation Academy (per NTSB report)
Operated by PAN AM INTERNATIONAL FLIGHT ACADEMY (per NTSB report)
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.
12 reports on file, 2014-01-09 – 2018-09-18.
Part: WIRE — DETERIORATED · airframe 20,927 hrs
DURING A SCHEDULED INSPECTION, FOUND THE POWER WIRE FOR THE START BADLY DETERIORATED WITH NUMEROUS BARE SECTIONS OF WIRE EXPOSED. THE WIRE APPEARS TO BE AUTOMOTIVE TYPE WIRE AND WAS SUPPLIED AS PART OF THE INSTALLATION KIT.
Part: CHANNEL — CRACKED (LT WING) · airframe 19,306 hrs
A CHANNEL IN THE LEFT WING WAS FOUND CRACKED. CHANNEL IS LOCATED INBOARD ON THE WING'S LOWER SURFACE AND IS RIVETED TO SKIN PANEL.
Part: MAGNETO — MALFUNCTIONED (LEFT) · airframe 19,064 hrs
PILOT COULD NOT START ENGINE AFTER SIX ATTEMPTS. INSPECTION BY MAINTENANCE PERSONELL REVEALED THE NEWLY INSTALLED LEFT MAGNETO WAS MALFUNCTIONING.
Part: WINDOW FRAME — CORRODED (BS 73) · corrosion level 2 · airframe 19,062 hrs
CORROSION WAS FOUND TO LEFT WINDSCREEN FRAME STRUTURE. CORRODED AREA WAS ALONG OUTBOARD, LOWER END OF WINDSCREEN. IT IS SUSPECTED THAT CORROSON WAS CAUSED BY LEAKAGE FROM IMPROPERLY FITTED WINDSCREEN OR CONDENSATION.
Part: TUBE — SPLIT (RT MLG TIRE) · airframe 18,902 hrs
THE RIGHT MAIN TIRE WENT FLAT AS THE PILOTS EGRESSED. VISUAL INSPECTION OF THE TIRE TUBE REVEALED A SLIT .125" IN LENGTH. THERE WERE NO FOLDS TO THE TUBE THAT WOULD HAVE CAUSED A HOLE TO APPEAR.
Part: BRACKET — CRACKED (ELT) · airframe 18,424 hrs
WHEN THE ELT WAS BEING REMOVED FOR INSPECTION, THE TECH DISCOVERED TWO, 2 INCH CRACKS NEXT TO THE NUTPLATES IN THE ELT MOUNTING BRACKET. THESE CRACKS CAN ONLY BE SEEN WHEN THE ELT TRAY IS REMOVED.
Part: CYLINDER HEAD — CRACKED (ENGINE) · airframe 17,102 hrs
BORESCOPE EXAMINATION REVEALED THE NR 2 CYLINDER HEAD WAS CRACKED. AFTER THE CYLINDER WAS REMOVED, CRACKING WAS SEEN AT THE LOWER SPARK PLUG HOLE. THE CYLINDER HEAD CASTING NR C-02284.
Part: CYLINDER HEAD — CRACKED (ENGINE) · airframe 17,102 hrs
BORESCOPE EXAMINATION REVEALED THE NR 4 CYLINDER HEAD WAS CRACKED. AFTER THE CYLINDER WAS REMOVED, CRACKING WAS SEEN AT THE LOWER SPARK PLUG HOLE. THE CYLINDER HEAD CASTING NR C-02908.
Part: CYLINDER HEAD — CRACKED (ENGINE) · airframe 17,102 hrs
BORESCOPE EXAMINATION REVEALED THE NR 3 CYLINDER HEAD WAS CRACKED. AFTER THE CYLINDER WAS REMOVED, CRACKING WAS SEEN AT THE LOWER SPARK PLUG HOLE AND AT THE EXHAUST VALVE SEAT. THE CYLINDER HEAD CASTING NR C-02883.
Part: CYLINDER HEAD — CRACKED (ENGINE) · airframe 17,102 hrs
BORESCOPE EXAMINATION REVEALED THE NR 1 CYLINDER HEAD WAS CRACKED. AFTER THE CYLINDER WAS REMOVED, CRACKING WAS SEEN AT THE LOWER SPARK PLUG HOLE. THE CYLINDER HEAD CASTING NR C-02859.
Part: PUMP — BLOCKED (FUEL SYSTEM) · airframe 16,022 hrs
DURING TAKEOFF, FUEL PRESSURE GAUGE GAVE A READING OF 0 PSI. THE ACFT HAD TO ABORT TAKEOFF AND RETURN TO RAMP AT DEPARTING AIRPORT. MAINTENANCE GROUND RAN ACFT WITH SAME RESULTS AND REPLACED THE ELECTRIC FUEL PUMP. AFTER THE FUEL PUMP WAS REPLACED, ACFT OPERATED NORMALLY. FURTHER INSPECTION OF THE ELECTRIC FUEL PUMP FOUND THE BALL VALVE AND BALL VALVE HOUSING TO BE SEVERELY WORN. THIS COULD HAVE CAUSED A FUEL BLOCKAGE WHICH IS CRITICAL DUE TO THE FUEL SYSTEM BEING CONNECTED IN SERIES.
Part: SENSOR — CONTAMINATED (ZONE 700) · airframe 15,608 hrs
THE PILOT WAS PERFORMING A PREFLIGHT ENGINE RUN, WHEN THE RIGHT MAG WAS SWITCHED OFF, THE ENGINE RAN ROUGH; RETURNED TO THE RAMP AND REPORTED THE PROBLEM. THIS AIRCRAFT IS EQUIPPED WITH AN ELECTRONIC IGNITION SYSTEM (EIS) INSTALLED IAW STC SA02987CH THAT INCORPORATES A COMPUTER, MAP SENSOR, COIL PACK, AND A TIMING HOUSING IN THE PLACE OF THE LEFT MAG. THE MAP SENSOR IS LOCATED UNDER THE CABIN FLOOR OF THE AIRCRAFT AND RECEIVES ITS MANIFOLD PRESSURE DATA FROM THE NR 3 CYLINDER INTAKE BY WAY OF A FLEXIBLE LINE. DURING TROUBLESHOOTING, THE MAP SENSOR AND MAP LINE WERE FOUND FILLED WITH ENGINE OIL. THE MAP SENSOR WAS REPLACED AND THE MAP LINE FLUSHED OUT; SUBSEQUENT ENGINE RUNS WERE SATISFACTORY.