N248JF
Registered owner: ZIPLINE INTERNATIONAL INC, CA (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
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.
2 reports on file, 2004-11-18 – 2006-06-23.
Part: PRESSURE SWITCH — FAILED (HYDRAULIC SYS) · airframe 4,287 hrs · 2,852 cycles
PILOT REPORTED LOSS OF NR 1 HYD FLUID, LEFT SIDE. TROUBLESHOOTING REVEALED THE LEFT HYDRAULIC SYSTEM PRESSURE SWITCH IN THE TAIL COMPARTMENT FOR THE HYDRAULIC SYSTEM RUPTURED INTERNALLY CAUSING THE FLUID/PRESSURE LOSS. REPLACED THE LEFT HYDRAULIC SYSTEM PRESSURE SWITCH WITH A NEW TYPE, IMPROVED UNIT. ALL SWITCHES AND BOTH HYDRAULIC PUMPS WERE ALSO CHANGED PER FALCON RECOMMENDATIONS. SUBSEQUENT OPERATIONAL AND LEAK CHECKS WERE CARRIED OUT. AIRCRAFT RETURNED TO SERVICE.
Part: CLAMP — LOOSE (BLEED AIR)
CLIMBING THROUGH 27,000 FT THE RT GENERATOR WENT OFFLINE, SHORTLY AFTERWARDS, LT GENERATOR WENT OFFLINE, AN EMERGENCY WAS DECLARED AND THE AC LANDED WITH NO FURTHER INCIDENT, INVESTIGATION FOUND A LOOSE CLAMP CONNECTING A BLEED AIR DUCT TO THE CABIN COLD TEMPERATURE CONTROL VALVE. IT IS SUSPECTED THAT BLEED AIR LEAKING AT THIS AREA CAUSED THE GENERATOR CONTROL UNITS TO STOP WORKING DUE TO OVERHEATING. THE CLAMP WAS TIGHTENED AND A LEAK CHECK PERFORMED. A FUNCTIONAL CHECK OF THE GENERATOR SYS PERFORMED. NO DISCREPANCIES WERE NOTED. GENERATOR CNTRL UNITS WERE REPLACED AS A PRECAUTIONARY MEASURE GCU`S WERE SENT TO THE MFG AND FOUND TO FUNCTION IAW DESIGN SPECIFICATION. (K)