N649DX
Registered owner: ASA PARTS LLC, TX (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DURING CRUISE FLIGHT, THE PILOT NOTED THAT THE GEAR HAD UNLOCKED FROM THE UP AND LOCKED POSITION AND OBSERVED A HYDRAULIC LOW PRESSURE CAS MESSAGE. THE PILOT DIVERTED TO BIRMINGHAM INTERNATIONAL AIRPORT, KBHM, WHERE HE LANDED WITHOUT FURTHER INCIDENT, ALTHOUGH HE HAD TO BE TOWED OFF OF THE ACTIVE RUNWAY. INVESTIGATION REVEALED THAT THE HYDRAULIC POWER PACK WAS FAILED. THE POWER PACK WAS REPLACED BY EMBRAER TECHNICIANS AND APPROVED FOR RETURN TO SERVICE TO RETURN TO HOME BASE, KRDG. THIS WAS THE 14TH POWER PACK INSTALLED IN THIS AIRCRAFT SINCE THE SPOILER INSTALLATION MODIFICATION PER EMBRAER S/B 500-00-0009 ON APRIL 2015.
PILOT POWERED UP THE AIRCRAFT AND IMMEDIATELY NOTED THE HYDRAULIC PUMP WAS CYCLING CONTINUOUSLY. PILOT PROCEEDED TO SHUT DOWN THE AIRCRAFT. CORRECTIVE ACTION INVOLVED INSTALLING AN OVERHAULED POWERPACK. OPERATIONAL CHECK WAS SATISFACTORY.
PILOT REPORTED THE HYDRAULIC PUMP WAS RAPIDLY CYCLING WHILE IN CRUISE FLIGHT. PILOT EXTENDED THE LANDING GEAR NORMALLY AND HYDRAULIC OPERATION RETURNED TO NORMAL. PILOT LANDED AT HIS DESTINATION WITHOUT FURTHER INCIDENT. CORRECTIVE ACTION INVOLVED REPLACING THE HYDRAULIC POWER PACK. SUBSEQUENT LANDING GEAR RETRACTION OPERATIONAL CHECKS WERE SATISFACTORY.
PILOT EXPERIENCED THE HYDRAULIC PUMP CYCLING CONTINUOUSLY TO HOLD PRESSURE, FOLLOWED BY PARTIAL GEAR EXTENSION. THE PILOT EXTENDED THE LANDING GEAR USING EMERGENCY PROCEDURES AND LANDED WITHOUT INCIDENT. CORRECTION ACTION INVOLVED REPLACING THE HYDRAULIC POWER PACK ASSEMBLY. SUBSEQUENT OPERATIONAL CHECKS WERE SATISFACTORY.
PILOT EXPERIENCED A TOTAL HYDRAULIC FAILURE. WITHOUT HYDRAULIC PRESSURE, THE LANDING GEAR FELL OUT AND CYCLED TO DOWN AND LOCKED. THE PILOT DIVERTED AND LANDED WITHOUT INCIDENT UTILIZING EMERGENCY BRAKES. REPLACED THE HYDRAULIC PUMP ASSEMBLY. THIS IS THE 4TH HYDRAULIC PUMP FAILURE IN THIS AIRCRAFT. GROUND SPOILER, SPEED BRAKE FUNCTION, AND NEW HYDRAULIC SYSTEM WAS INSTALLED.
HYDRAULIC PUMP FAILED IN FLIGHT.
LOW HYD CAS, HYDRAULIC PRESSURE DROPPED TO 800 PSI IN FLIGHT. HYDRAULIC POWER-PACK ASSEMBLY WAS FOUND TO BE FAILED.
WHILE CRUISING AT 22,000 FT, PILOT EXPERIENCED HYD AUTO PRESSURE FLUCTUATION BETWEEN 1600/3200. HYD ON, PRESSURE FLUCTUATIONS AND SPIKES TO 3800. HYD OFF, PRESS 0 AND LANDING GEAR FALLS OUT. PILOT LANDED WITH HYD PRESSURE ON AND SEEING PRESSURE FLUCTUATIONS AND SPIKES TO 3800. ALSO DURING PRESSURE FLUCTUATIONS, THUMPING/BUMPING NOISE/VIBRATION AT PILOT FLOOR - FORWARD. INVESTIGATION DISCLOSED THE HYDRAULIC PUMP FAILED. HYDRAULIC POWER PACK VENTILATION FAN WAS ALSO FOUND FAILED. REPLACED FAULTY COMPONENTS; OPERATIONAL CHECKS WERE SATISFACTORY.
DURING A POST FLIGHT INSPECTION, DISCOVERED PLATING MATERIAL ON THE INLET LIP SURFACE WAS SEPARATING FROM THE LIP AND HAD FLARED BACKWARDS INTO THE THROAT OF THE PITOT TUBE. THE PITOT TUBE WAS REMOVED FROM THE ACFT AND THE PITOT LINE WAS CLEARED OF DEBRIS. THE DEBRIS WAS COLLECTED FROM THE INSIDE OF THE PITOT TUBE AND FROM THE PITOT LINE ITSELF. THE DEBRIS WAS MOSTLY SMALL, COPPER COLORED, METALLIC PARTICULATES WITH ONE LARGER PIECE OF PLATING MATERIAL. A NEW PITOT TUBE WAS THEN INSTALLED AND THE PITOT/STATIC SYS RECERTIFIED. AS WITH THE OTHER INSTANCES OF THIS OCCURENCE, THE FOD WAS LOCATED INSIDE THE PROBE OR THE IMMEDIATE PITOT LINE. NO FOD WAS COLLECTED FROM FURTHER BACK IN THE PITOT LINE.
DURING THE FIRST SCHEDULED INSP (600HR/12 MONTH) THE RT ENGINE FUEL FILTER WAS FOUND TO HAVE NEVER BEEN INSTALLED AT THE FACTORY. THE MFG WAS NOTIFIED AND THEY REQUESTED AN ENGINE HOT SECTION BOROSCOPE INSP BE PERFORMED. NO ENGINE DISTRESS WAS OBSERVED AND CONTINUED OPERATION WAS AUTHORIZED FOLLOWING INSTALLATION OF A FILTER A 30 MINUTE PERFORMANCE RUN AT 80 PERCENT POWER. NO DISCREPANCIES WERE NOTED. SEVERAL DAYS LATER, THE MFG CONTACTED THE OPERATOR AND REQUESTED THE FUEL CONTROL BE REMOVED FOR INSPECTION. AN EXCHANGE FCU WAS PROVIDED AND INSTALLED ON THE ENGINE.