N915FG
Registered owner: FGF SOVEREIGN 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
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.
8 reports on file, 2014-01-05 – 2022-05-01.
Part: PUMP — FAILED · airframe 3,846 hrs · 2,144 cycles
THE FLIGHT CREW REPORTED LEFT HYDRAULIC LOW PRESSURE MESSAGE IN FLIGHT. THE FLIGHT WAS DIVERTED AND LANDED WITHOUT INCIDENT. THE MAINTENANCE VENDOR TROUBLESHOT AND DETERMINED THE LEFT HYDRAULIC PUMP WAS DEFECTIVE. THE PUMP WAS REMOVED AND REPLACED THE HYDRAULIC PUMP AND FILTERS AS REQUIRED. OPS CHECKS AND LEAK CHECKS WERE SATISFACTORY AND THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: BLEED AIR SYS — LEAKING · airframe 3,783 hrs · 2,107 cycles
THE FLIGHT CREW REPORTED THAT THE RIGHT SUPPLY BLEED LEAK INDICATOR ILLUMINATED. WAS UNABLE TO CLEAR THE FAULT PER CHECKLIST. THE MAINTENANCE VENDOR TROUBLESHOT AND INSTALLED NEW ORING ON COMPRESSOR OUTLET DUCT. OPS CHECKS WERE SATISFACTORY AND THE AIRCRAFT WAS RETURNED TO SERVICE .
Part: WINDOW — CRACKED (COCKPIT) · airframe 3,381 hrs · 1,880 cycles
LEFT WINDOW IN COCKPIT CRACKED DURING FLIGHT
Part: SPAR CAP — CORRODED (RT WING) · airframe 2,870 hrs · 1,584 cycles
DURING INSPECTION, THE VERTICAL STEM OF THE LOWER REAR SPAR CAP AFT ANGLE - RH OF THE REAR SPAR ASSEMBLY WAS FOUND TO BE CORRODED AT ABOUT CWS 325 WITH .078" REMAINING THICKNESS ON THE WEB STEM FLANGE. REPAIR DEFINITION WAS RECEIVED FROM CESSNA ENGINEERING TO REPAIR CORRODED AREA BY BLENDING / ALODINE TREATMENT / PRIMER APPLICATION. REPLACEMENT OF RIVETS WERE NECESSARY UPON REASSEMBLY WITH NEW RIVETS.\ IN THE AREA
Part: BEAM — CORRODED (VERTICAL STAB) · airframe 2,870 hrs · 1,584 cycles
CORROSION WAS FOUND AT MULTIPLE SITES ON THE VERTICAL STABILIZER REAR SPAR CAPS. AFTER BLENDING, THE REMAINING THICKNESS AT EACH SITE WAS MEASURED USING ULTRASOUND. ALL CORROSION DAMAGE WAS REMOVED BY BLENDING AND CESSNA ENGINEERING ISSUED A REPAIR DEFINITION AND APPROVAL FOR REMAINING THICKNESS TO REMAIN IN SERVICE. FINAL METAL TREATMENT WAS CARRIED OUT USING ALODINE, PRIMER AND TOP COAT.
Part: SKIN — CORRODED (RT WING) · corrosion level 2 · airframe 2,520 hrs · 1,373 cycles
DURING A SCHEDULED INSPECTION, MICROBIAL GROWTH WAS FOUND IN THE CENTER TANKS. AFTER CLEANING THE TANKS, CORROSION WAS FOUND ON THE LOWER SKIN AND CONNECTING STRUCTURE.
Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 1,940 hrs · 1,057 cycles
GEAR UNLOCK LIGHT STAYS ON AFTER GEAR RETRACTION. CYCLED GEAR & LIGHT EXTINGUISHED.
Part: VALVE — DEGRADED (ACM SYSTEM) · airframe 1,675 hrs · 899 cycles
AT 11,000 FEET & 40 MILES FROM HOU. THERE WAS A POP SOUND WITH AN AMBER CAS MESSAGE OF ACM BLEED LEAK & A BLUE CAS MESSAGE BAGGAGE HEAT OFF. A FEW SECONDS LATER THERE WAS THE SMELL OF SMOKE IN THE COCKPIT. NEVER SAW THE CAS MESSAGE FOR EMERGENCY PRESSURIZATION ON.