N546QS
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.
15 reports on file, 1998-03-01 – 2020-12-11.
Part: FUEL/OIL COOLER — FAILED (ENGINE) · airframe 12,105 hrs · 4,736 cycles
ABOUT 30 MINUTES INTO THE FLIGHT WE NOTICED A FUEL IMBALANCE WITH THE LEFT SIDE BEING LOW. SHORTLY THEREAFTER WE GOT THE BLUE "FUEL IMBALANCE" CAS MESSAGE. THE IMBALANCE CONTINUED TO INCREASE DURING THE FLIGHT. BOTH ENGINE WERE RUNNING EVEN AND STABLE. AIPLANE WAS FLYING LEVEL WITH NO ROLL TRIM REQUIRED, LEADING TO BELIEVE THAT AN INDICATION WAS THE ISSUE. CALCULATIONS SHOWED ADEQUATE FUEL FOR LANDING IF IT WAS A LEAK. AFTER LANDING AND PARKING WE OBSERVED THE ACTIVE LEAK OUT OF THE BOTTOM OF THE LT COWL AT A RATE OF CLOSE TO AN OPEN WATER HOSE WITHOUT SPICKET. THIS AFTER THE ENGINE WAS SHUT DOWN. THE PLANE WAS IMMEDIATELY COMPLETELY SHUT DOWN. LEAKAGE WAS STILL OBSERVED ABOUT 8-10 MINUTES AFTER SHUT DOWN, FROM COWL AND SOME DRIPING ON FUSELAGE AROUND VHF1 COMM ANTENNA. FUEL SPILL WAS RAPIDLY CONTAINED BY FBO PERSONNEL. PICTURES ATTACHED. SIGNOFF. POWERED AIRCRAFT WITH APU POWER. OPENED LOWER ENGINE COWLINGS TO PERFORM INSPECTIONS ON LT ENGINE AND FOUND FUEL LEAKS ALL AROUND LOWER ENGINE COWLINGS. PERFORMED OPERATIONAL CHECK OF LT WET MOTOR OPERATION AND FOUND THE LT ENGINE LOW PRESSURE FUEL FILTER TO BE LEAKING EXCESSIVE. TURN THE LT ENGINE OFF AND WAITED TO COOL OFF. PERFORMED VISUAL INSPECTION ON LP FUEL FILTER AND FOUND THE ORIGINAL TO BE VISUAL FROM FUEL FILTER COVER. ALL WORK IN REF TO GSSO AMM 73-12-01. REMOVED AND REPLACED LT FUEL COOLED OIL COOLER, IAW RR BR71CRC4 EMM 79-22-01. FUELED LT WING TO 3300 LBS. RAN LT ENGINE, IAW QRH AND PERFORMED OPERATIONS CHECK WITH NO DEFECTS NOTED. SERVICED LT ENGINE WITH 2.5 QUARTS OF 2380. FILLED OIL REPLENISHER TO FULL, IAW G550 AMM 12-14-01.
Earlier reports · 1998–2018 · 14 reports
2018
Part: SHAFT — CORRODED (TE FLAP DRIVE) · corrosion level 3 · airframe 10,618 hrs · 4,047 cycles
RIGHT FLAP NR 1 TORQUE SHAFT CORRODED.
Part: FITTING — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 10,618 hrs · 4,047 cycles
HORIZONTAL STABILIZER PIVOT FITTING HAD CORROSION IN THE BORES.
2016
Part: COVER — DAMAGED (RT WING TE FLAP) · airframe 8,655 hrs · 3,158 cycles
THE RT FLAP HAS THE B TRACK COVER PANEL BENT AND DEFORMED EXCEEDING THE LIMITS OF SERVICEABILITY.
Part: SKIN — DELAMINATED (SPOILER) · airframe 8,655 hrs · 3,158 cycles
DURING CB164 PART 1, TAP TEST INSPECTION NOTED A DELAMINATED AREA AROUND THE RT GROUND SPOILER BOARD THROW BOARD ATTACHMENT HOLE. REPLACED.
2014
Part: SWITCH — FAILED (NLG WOW) · airframe 6,124 hrs · 2,135 cycles
NOSE WOW AMBER LIGHT ON AFTER TAKOFF, DURING GEAR EXTENTION OBTAINED THREE GREEN INDICATIONS & MAINS IN STILL IN AIR MODE NORMAL & NOSE IN GROUND. NOSE WHEEL STEERING FAIL AMBER CASE LIGHT WAS THEN DEALT WITH & LANDED WITH NOSE WHEEL STEERING OFF. AFTER STOPPING & CYCLING NWS ALL WORKED WELL. REMOVED NOSE GEAR WOW SWITCH AND INSTALLED A NEW SWITCH. WORK DONE IAW AMM 32-60-00, 32-62-03 & 07-10-00. OPS TESTED GOOD AT THIS TIME.
2012
Part: WARNING MESSAGE — ILLUMINATED (RT MLG) · airframe 3,733 hrs · 1,227 cycles
AFTER TAKEOFF, DURING GEAR RETRACTION, HAD AN AMBER CAS "RT MAIN GEAR DOOR OPEN" MESSAGE. DURING EXTENSION, HAD THE SAME MESSAGE PLUS AN AMBER CAS "R MAIN GEAR NOT DOWN". THESE MESSAGES ARE ONLY THERE FOR LESS THAN 2 SECONDS, THEN INDICATIONS RETURN TO NORMAL. GEAR SWINGS CARRIED OUT, DEFECT CONFIRMED. CARRIED OUT MLG ADJUSTMENT TEST 1 MAIN GEAR. RIGGING ADJUSTMENT REF MM 32-10-00, REV 20. CARRIED OUT LANDING GEAR CYCLING. OPS TEST REF MM REV 20 CEAR NOW "SATS". CAS MESSAGE NO LONGER APPEARS.
2010
Part: UNKNOWN — ODOR (CABIN) · airframe 2,330 hrs · 806 cycles
CREW REPORTED SMOKE/BURN ODOR IN BAGGAGE COMPARTMENT AFTER FINDING THE RT CREW CIRCUIT BREAKER POPPED. INSPECTED 60HZ CB PANEL. RAN ALL CABIN SYS, AND DREW POWER FROM GALLEY AND CREW REST 60HZ OUTLETS FOR EXTENDED PERIODS OF TIME WITH NO DISCRPANCIES FOUND, AND NO SIGN OF SMOKE. INSPECTED AC POWER CONTROLLER WITH NO DEFECTS.
2006
Part: WARNING LIGHT — UNKNOWN (FUEL SYS) · airframe 9,156 hrs · 6,083 cycles
AUX TRANSFER LIGHT ILLUMINATED, TAKE OFF ABORTED. ITEM IS UNDER INVESTIGATION.
2005
Part: LANDING GEAR — INOPERATIVE (RT MLG) · airframe 8,651 hrs · 5,731 cycles
RED LANDING GEAR LIGHT ON THE RIGHT SIDE (RIGHT MAIN) STAYED ON AFTER GEAR RETRACTION, WITNESS ON THE GROUND REPORTED THAT THE RIGHT MAIN GEAR NEVER RETRACTED. ITEM IS UNDER INVESTIGATION.
Part: WARNING LIGHT — MALFUNCTIONED (MLG) · airframe 8,649 hrs · 5,729 cycles
RED LANDING GEAR UNSAFE LIGHT ON THE RIGHT SIDE STAYED LIT AFTER GEAR RETRACTION. EXCESS WIND NOISE AND SLIGHT VIBRATION WAS NOTICED WHILE AIRBORNE. VISUALLY INSPECTED RT MAIN GEAR, INSPECTED MICRO SWITCHES & WIRING HARNESS AT SWITCH & TERMINAL BLOCK, NO DEFECTS NOTED. JACKED AIRCRAFT CYCLED GEAR SEVERAL TIMES. NO DEFECTS NOTED ALL WORK IAW HAWKER 1000 MM 32-30-00.
2003
Part: SOLENOID — FAILED (LT ENGINE) · airframe 6,983 hrs · 4,605 cycles
AFTER STARTED TAXIING, HEARD POPPING NOISE FROM LT ENGINE, ITT RAPIDLY CLIMBED TO 710 DEGREES OIL 1 LOW PRESSURE CAME ON, SHUTDOWN THE LEFT ENGINE. REMOVED & REPLACED THE 3 OâCLOCK AND 9 OâCLOCK 2.8, 2.5 BOVâS AND BOV SOLENOID IAW RAYTHEON HAWKER 1000 AMM CHAP 75-30-00. PERFORMED FUEL SAMPLE AND INSPECTED FUEL FILTER, ALL CHECKED GOOD. ACCOMPLISHED ENGINE RUN, OPS CHECKED GOOD IAW PWC 305 MM CHAPTER 71-00-00.
2000
Part: CONNECTOR — MELTED (RADOME)
NOSE TAXI LIGHTS CONNECTOR DESIGNATOR NTD, HAVE BEEN FOUND MELTED TOGETHER AND SIGNS OF ARCING (INTERNALLY). THE PINS TO THIS CONNECTOR ARE EXPOSED TO MOISTURE IN THE RADOME. CONNECTOR IS LOCATED IN THE VICINITY OF OXYGEN BOTTLES. (X)
Part: CONNECTOR — MELTED (RADOME)
NOSE TAXI LIGHTS CONNECTOR DESIGNATOR NTD, HAVE BEEN FOUND MELTED TOGETHER AND SIGNS OF ARCING (INTERNALLY). THE PINS TO THIS CONNECTOR ARE EXPOSED TO MOISTURE IN THE RADOME. CONNECTOR IS LOCATED IN THE VICINITY OF OXYGEN BOTTLES. (X)
1998
Part: PULLEY — BINDING (ELEV CABLE)
CONTROL COLUMN IS STIFF IN MOVEMENT FORE AND AFT. FOUND ELEVATOR CABLE PULLEY UNDER CHART CASE FLOOR (P/N F46) RUBBING FORWARD STATIC LINE. REPOSITIONED LINE.