N550QS
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| NETJETS AVIATION, INC. (DXTA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
GSD FAIL 2 AMBER CAS: LEVEL AT FL450 WE FELT AND HEARD A LIGHT AERODYNAMIC HUM VIBRATION FOLLOWED BY AMBER X'S ON AILERON TRIM INDICATOR, RUDDER TRIM INDICATOR AND LEFT SPOILER POSITION DISPLAY. LEFT HYDRAULIC SYNOPTICS PAGE INTERMITENTLY SHOWED NO HYDRAULIC PRESSURE FROM LEFT PUMP BUT SYSTEM PRESSURE AND QUANTITY NORMAL. AMBER RA FAIL DISPLAYED ON BOTH LEFT AND RIGHT PFDS. A FEW MINUTES LATER, WE RECEIVED A CONTINUOUS AUDIBLE " GROUND PROXIMITY WARNING FAIL" THE MASTER WARNING ACTIVATED AND CYCLED CONTINUOUSLY DISPLAYING ALL AND AT TIMES JUST SOME OF THE FOLLOWING AMBER CAS MESSAGES, BLEED AIR MON R, BLEED AIR MON L, CABIN ALT, RUDDER BIAS FAULT, AILERON CNTRL FAULT, AND GROUND PROX FAIL. THE LANDING GEAR POSITION CHANGED TO AMBER X'S. THE FUEL QUANTITY PANEL CHANGED TO AMBER DASHES. IN ADDITION WE RECEIVED WHITE CAS MESSAGES NO STANDBY DATA WHILE THE STANDBY FLIGHT DISPLAY APPEARED TO BE OPERATING NORMALLY. ALSO RECEIVED, WHITE CAS MESSAGE FDR FAIL. DESCENDING THRU APPROXIMATELY 14,000 MSL ALL ABNORMAL INDICATIONS STOPPED. THE LANDING GEAR WAS EXTENDED NORMALLY. NO BLOW DOWN PROCEDURE PERFORMED. CABIN TEMPERATURE CONTROL REMAINED NORMAL, PRESSURIZATION INDICATIONS REMAINED NORMAL. SYSTEMS ALL APPEARED TO BE OPERATING BUT INDICATING AND MONITORING AT FAULT. CORRECTIVE ACTION: REPAIRED DCU #2. OPS CHECK GOOD. IAW CESSNA MODEL 680A AMM 31-40-10
MAIN DOOR GAS STRUT SNAPPED IN TWO PIECES. MAIN CABIN DOOR STILL OPERATES NORMALLY. NO BINDING OBSERVED ARRIVED ON SITE AND GAINED ACCESS TO THE AIRCRAFT. OPENED THE MED AND FOUND THE SUPPORT STRUT LOWER ROD SEPARATED FROM THE MIDDLE AND UPPER TUBES. FOUND THAT THE UPPER PART OF THE ROD HAS BEEN BROKEN OFF AND REMAINS INSIDE THE MIDDLE TUBE. ALSO FOUND THE AFT DOOR COVER ASSEMBLY TO ALSO BE DAMAGED. CLOSED THE MED. LOOKED AT THE TRACKING ON RAMP AND FOUND THAT THERE IS NO TRACKING ON THE SUPPORT STRUT ASSY. SENT UPDATE TO MCC. THEY NOTIFIED US THAT THE SUPPORT STRUT ASSY IS ON "PRODUCTION PULL" STATUS AT TEXTRON. MCC REQUESTED THAT WE REMOVE THE STRUT ASSY AND SEE IF WE CAN REPAIR BY REPLACING THE LOWER ROD AND TO MAKE SURE THERE IS NO DAMAGE TO THE MIDDLE TUBE WHICH IS ALSO ON "PRODUCTION PULL" STATUS AT TEXTRON. REMOVED THE PIECES OF THE SUPPORT STRUT ASSEMBLY FROM THE AIRCRAFT. SEPARATED THE PIECES FOUND THE RUB RING AROUND THE UPPER END OF THE INNER ROD ASSEMBLY WAS MISSING CAUSING SIGNIFICANT WEAR ON THE ROD END AND INSIDE OF THE MIDDLE TUBE WHICH CAUSED BINDING AND RESULTED IN THE UPPER END OF THE ROD BREAKING OFF INSIDE THE MIDDLE TUBE. NOTED THAT THE MIDDLE TUBE DOES NOT SLIDE IN THE UPPER TUBE SMOOTHLY. REMOVED PIVOT SHAFT RETAINER PORTION OF THE OLD SUPPORT STRUT ASSEMBLY. INSTALLED NEW SUPPORT STRUT ASSEMBLY, REMOVED DAMAGED COVER ASSEMBLY, AND INSTALLED NEW MED AFT COVER ASSY. COMPLETED INSTALL OF THE AFT SUPPORT STRUT ASSEMBLY. OPS CHECKS GOOD. ALL WORK PERFORMED IN ACCORDANCE WITH AMM 52-10-40.
MAIN DOOR GAS STRUT SNAPPED IN TWO PIECES. MAIN CABIN DOOR STILL OPERATES NORMALLY. NO BINDING OBSERVED ARRIVED ON SITE AND GAINED ACCESS TO THE AIRCRAFT. OPENED THE MED AND FOUND THE SUPPORT STRUT LOWER ROD SEPARATED FROM THE MIDDLE AND UPPER TUBES. FOUND THAT THE UPPER PART OF THE ROD HAS BEEN BROKEN OFF AND REMAINS INSIDE THE MIDDLE TUBE. ALSO FOUND THE AFT DOOR COVER ASSEMBLY TO ALSO BE DAMAGED. CLOSED THE MED. LOOKED AT THE TRACKING ON RAMP AND FOUND THAT THERE IS NO TRACKING ON THE SUPPORT STRUT ASSY. SENT UPDATE TO MCC. THEY NOTIFIED US THAT THE SUPPORT STRUT ASSY IS ON "PRODUCTION PULL" STATUS AT TEXTRON. MCC REQUESTED THAT WE REMOVE THE STRUT ASSY AND SEE IF WE CAN REPAIR BY REPLACING THE LOWER ROD AND TO MAKE SURE THERE IS NO DAMAGE TO THE MIDDLE TUBE WHICH IS ALSO ON "PRODUCTION PULL" STATUS AT TEXTRON. REMOVED THE PIECES OF THE SUPPORT STRUT ASSEMBLY FROM THE AIRCRAFT. SEPARATED THE PIECES FOUND THE RUB RING AROUND THE UPPER END OF THE INNER ROD ASSEMBLY WAS MISSING CAUSING SIGNIFICANT WEAR ON THE ROD END AND INSIDE OF THE MIDDLE TUBE WHICH CAUSED BINDING AND RESULTED IN THE UPPER END OF THE ROD BREAKING OFF INSIDE THE MIDDLE TUBE. NOTED THAT THE MIDDLE TUBE DOES NOT SLIDE IN THE UPPER TUBE SMOOTHLY. REMOVED PIVOT SHAFT RETAINER PORTION OF THE OLD SUPPORT STRUT ASSEMBLY. INSTALLED NEW SUPPORT STRUT ASSEMBLY, REMOVED DAMAGED COVER ASSEMBLY, AND INSTALLED NEW MED AFT COVER ASSY. COMPLETED INSTALL OF THE AFT SUPPORT STRUT ASSEMBLY. OPS CHECKS GOOD. ALL WORK PERFORMED IN ACCORDANCE WITH AMM 52-10-40.
LAV EXIT SIGN/LIGHT: SOME EMERGENCY LIGHTING IS INOPERATIVE. EXIT SIGN ON BULKHEAD BEHIND SEAT 7, EXIT SIGN ON TOILET FACE PANEL, DOWN LIGHTS AT TOILET BASE ARE ALL INOP. PACK WAS CHARGED FOR 30 MINUTES ON APU WITH NO CHANGE. CORRECTIVE ACTION; REPLAED FAULTY #4 EMERGENCY LIGHTING BATTERY. CHARGED BATTERY AS REQUIRED. PERFORMED OPS. CHECK OF EMER. LIGHTS, OPS. GOOD.WORK DONE IN REFERENCE TO CESSNA CE-680 AMM 33-50-10.
RIGHT WING INSPECTION LIGHT, #3SEAT OVERHEAD AND UNDERSEAT LIGHTS INOP. WILL NOT RECHARGE USING EMER LIGHTS FAIL PREFLIGHT TEST PROCECEDURE GAINED ACCESS TO #2 EMERGENCY LIGHTING BATTERY PACK. UPON FURTHER INVESTIGATION. FOUND THAT THE FUSE WAS NOT INSERTED CORRECTLY INTO THE BATTERY PACK. GLASS FUSE WAS GOOD. RE-INSERTED FUSE INTO BATTERY PACK AND SECURED IN PLACE. MULTIPLE EMERGENCY LIGHTING BATTERY PACK POST-MAINTENANCE CHECKS GOOD, ALL WORK DONE IAW CE-680A SPM 20-30-25. NO FURTHER DEFECTS NOTED.
PNEUMATIC DISTRIBUTION: NON ELECTRICAL FUMES SMELT AFTER TAKEOFF. LASTED FOR 2-3 MINUTES. REMOVED WORN HEPA FILTER P/N 9914836-1 S/N 0948 AND REPLACED WITH NEW UNIT. ALL WORK DONE WITH REFERENCE TO C680A-AMM-21-70-10.
MAIN DOOR: MAIN CABIN DOOR WILL NOT CLOSE. THE LIFT MOTOR KEEPS FAILING. THE DOOR WILL NOT EVEN COME UP HALF WAY. FOUND INNER DOOR HANDLE OPEN PROX SWITCH(SC006) TO BE INTERMITTENT. REMOVED AND REPLACED PROX SWITCH(SC006) IAW CE680A MM 52-70-10. OPS CHECKS GOOD. OLD/NEW PN: S2800-1257
CABIN DOOR MOTOR FAILS TO FULLY CLOSE MAIN CABIN DOOR. FAILED SEVERAL ATTEMPT WITH OVERIDE. THE DOOR MOTOR WILL LIFT THE DOOR ABOUT A FOOT AND THEN SHUTS OFF. AMBER CHECK DOOR HANDLE LIGHT ILLUMINATED ON EXTERIOR. DISCOVERED WHEN THE NICAD BATTERIES ARE IN A CHARGING STATE VIA. EXTERNAL OR APU POWER THE NEW OVERCURRENT LIMIT PARAMETER DETECTION SYSTEM IN THE MAIN CABIN DOON CONTROL PCB, COULD PREVENT THE MAIN CABIN DOOR FROM CLOSING. CLOSE MAIN CABIN DOOR USING NORMAL CLOSING PROCEDURES. OPS CHECK GOOD. WORK DONE IN REF WITH CE-680A 52-10-00. NO DEFECTS NOTED.
AFTER GEAR RETRACTED SUCCESSFULLY & CLIMBING ABOVE FL 400, FELT A THUMP IN NOSE. RECEIVED MAINS UP & NLG MISCOMPARE AMBER MESSAGE. DESCENDED TO A LOWER ALTITUDE. FELT MORE STUTTERING THUMPS. AFTER THAT A RHYTHMIC THUMPING. LOWERED FLAPS 1 & ABOUT TO LOWER GEAR WHEN IT STOPPED & SHOWED UP. LANDED SAFELY. NO DAMAGE TO NLG OR BAY. DISCONNECTED DOORS, PERFORMED GEAR SWINGS. FOUND NLG UPLOCK SWITCH NOT ENGAGING. PERFORMED GEAR BUMP TROUBLESHOOTING. CHECKED PSI OF UPPER & LOWER BARREL. FOUND BOTH BARRELS LOW PSI. SERVICED UPPER & LOWER BARREL OF NLG STRUTE. MEASURED STRUT LENGTH & FOUND GOOD, RECONNECTED NLG DOORS & PERFORMED SWINGS, GOOD WITH UPLOCK ENGAGING PROPERLY. WORK DONE IAW AMM 32-00-00,12-10-52.
EMER LIGHTS WILL NOT COME ON WHEN SWITCH SELECTED TO ON WITH ACFT POWERED DOWN. PREFLIGHTED WITH THE AIRPLANE POWERED UP, THEN POWERED DOWN TO WAIT. AFTER POWERING DOWN, I CHECKED THE EMER LIGHTS AND FOUND NORMAL OPERATION. AFTER WAITING AN HOUR, WE CAME OUT TO POWER UP, AND TESTED EMER LIGHTS AGAIN AND FOUND THAT WITH AIRCRAFT POWER OFF, THE EMER LIGHTS WOULD NOT WORK WHEN SELECTED TO ON. THEY WOULD WORK WHEN SELECTED TO ARM. WHEN THE AIRCRAFT WAS POWERED UP, THE LIGHTS WOULD WORK IN BOTH ON AND ARM. REMOVED AND REPLACED #4 EMERGENCY LIGHT BATTERY PACK IAW CE·680A MM 33-50-06, PERFORMED OPERATIONAL TEST, NO DEFECTS NOTED.
DURING PRE-FLIGHT TEST OF EMERGENCY LIGHT SYSTEM(BEFORE POWERING UP), NOTICED EXIT SIGN AT SEAT 7, EXIT SIGN BELOW LAV SEAT, AND FLOOR LIGHT BELOW LAV SEAT, WOULD NOT ILLUMINATE. ALL OTHER EMERG LIGHTS FUNCTION NORMALLY. THIS IS A REPEAT WRITE UP. VERIFIED PILOT WRITE UP. COMPLIED WITH TASK CARD TC-FLT-33-1001 BY ALLOWING THE EMERGENCY LIGHT BATTERIES TO CHARGE FOR 60 MINUTES. PERFORMED DISCHARGE OF THE EMERGENCY LIGHT POWER SUPPLY BATTERIES, ALL LIGHTS REMAIN ILLUMINATED LONGER THAN 10 MINUTES. PER TASK CARD TC·FLT-33-1001 THE BATTERIES ARE AIRWORTHY. RE- CHARGED FOR 60 MINUTES, CALLED MCC OF FINDING AND THEY ELECT TO SIGN OFF ALL WORK WAS DONE AS PER AMM 33-50-00.
EMERG EXIT SIGN/LIGHT: DURING PREFLIGHT, FOUND 3 LIGHTS THAT ARE NOT LIGHTING UP DURING THE EMERGENCY LIGHT TEST. THE WHITE EXIT SIGN ON THE BULKHEAD BEHIND SEAT 7. THE EXIT SIGN BELOW THE LAV SEAT. THE FLOOR LIGHT BELOW THE LAV SEAT. PERFORMED EMERGENCY LIGHTING OPERATIONAL CHECK IN ACCORDANCE WITH MODEL 680A MAINTENANCE MANUAL 33-50-00 WITH NO DEFECTS NOTED,
COMBUSTION CHAMBER DRAIN BOSS DETACHED WHILE FUEL DRAIN VALVE WAS REMOVED ON LH ENGINE. P&WC DEVIATION LETTER WAS ACCOMPLISHED DEVIATION LETTER DAA2023-1044-PW306D1-CN0086, CRM CASE: PWC-285022-Z8X0 DATED AUGUST 23, 2023. DEVIATION LETTER FOR ENGINE MODEL PW306D1 SERIAL NUMBER CN0124 (TTSN 6329.5 HRS, TCSN: 4163 CYCLES)- COMBUSTION CHAMBER DRAIN BOSS TEMPORARY REPAIR. FOR CONTINUED OPERATION UNTIL NEXT ENGINE SHOP VISIT.
EMERGENCY EXIT OPEN AMBER CAS: AMBER EMERGENCY EXIT OPEN CAS MESSAGE CAME ON APPROX ONE HOUR INTO FLIGHT AT FL410. EXTINGUISHED DURING DESCENT BELOW FL180 // SIGNOFF// COMPLIED WITH GVI AND MULTIPLE OPS CHECKS OF EMERGENCY EXIT DOOR WITH NO DEFECTS NOTED AT THIS TIME, INSPECTED DOOR LOCK PIN AND PROXIMITY SENSOR, NO DEFECTS NOTED REF CITATION MODEL 680A AMM S2-20--00, PERFOMED AIRCRAFT PRESSURAZATION PER MCC REQUEST NO UNCOMMANDED DOOR CAS MESSAGES PRESENT REF CITATION MPDEL 680A AMM 21-30-00
GOUGE IN FUSELAGE SKIN UNDER FWD RH OVERWING SPLICE STRAP REPAIR.
GOUGES ON THE LH AND RH MLG SIDE BRACE FITTINGS (P/N'S 6922928-1 AND 6922928-2). ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DATED DECEMBER 21, 2021 DQ 32902 M1; 680A-0150 LH AND RH MLG SIDE BRACE ATTACH FITTINGS.
GOUGES ON THE LH AND RH MLG SIDE BRACE FITTINGS (P/N'S 6922928-1 AND 6922928-2). ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DATED DECEMBER 21, 2021 DQ 32902 M1; 680A-0150 LH AND RH MLG SIDE BRACE ATTACH FITTINGS.
LH ENGINE GEARBOX AFT COVER CORRODED IN MULTIPLE LOCATIONS.
RH ENGINE GEARBOX AFT COVER CORRODED IN MULTIPLE LOCATIONS.
DURING RETRACTION OF THE GEAR, GEAR DISAGREE CAS MESSAGE ILLUMINATED. THE NOSE GEAR DISPLAY BOX ON PFD WAS ALSO SHADED WITH AMBER LINES. BLEW GEAR DOWN BEFORE LANDING IAW CHECKLIST. INDICATED THREE GREEN FOR LANDING, AND LANDING WAS NORMAL. CAS MESSAGE DISAPPEARED WHEN THREE GREEN WERE INDICATED. RESET LANDING GEAR CONTROL VALVE. PERFORMED GEAR SWINGS WITH NO FAULTS. BLEED LANDING GEAR IAW 12-10-30. REMOVED LANDING GEAR CONTROL MANIFOLD, INSTALLED INSPECTED MANIFOLD ASSY, ALL WORK DONE IAW MM 32-30-20. INSTALLED A NEW CHECK VALVE TEE FITTING, CYCLED GEAR SEVERAL TIMES, NO DEFECTS NOTED, COMPLIED WITH EMERGENCY BLOW DOWN FUNCTION CHECK, RESET SYSTEM, NO DEFECTS NOTED, WORK DONE IAW MM 32-30-20. CYCLED LANDIN
REPEAT WRITEUP, DURING NORMAL TAXI SPEED, WHEN BRAKES APPLIED AIRCRAFT VEERED LEFT.
REPEAT WRITE-UP. AFTER LOW SPEED 60KT ABORTED TAKEOFF, LEFT BRAKE ASSEMBLY WAS VERY HOT AND SMOKING. LARGE TEMP DIFFERENCE BETWEEN LEFT (HOT) AND RIGHT (COOLER) BRAKES. NO DRAG OR SWERVE FELT AS BRAKES WERE APPLIED. PERFORMED ALL MAINTENANCE PROCEDURE CHECKS, CHECKED OK. TAXI CHECKED OK, NO DISCREPANCIES NOTED. WORK DONE IAW HAWKER 1000 MM CH 32-40-00.
T/O ROLL ABORTED FOR ENG/FUEL LOOK UP LIGHT. ITEM IS UNDER INVESTIGATION.
WHILE CLIMBING THROUGH FL250 SELECTED ENGINE ANTI ICE ON, SHORTLY THEREAFTER NOTICED A STRONG BURNING SMELL IN THE COCKPIT. DE-SELECTING ANTI ICE, SMELL WENT AWAY, NO VISIBLE SMOKE WAS NOTICED. OPS CHECKED ANTI ICE SYSTEM, SYSTEM OPS CHECK GOOD IAW HAWKER 1000 MM CHAPTER 75-10-00.
CLIMBING THROUGH APPROXIMATELY FL280, EXPERIENCED A SEVERE LONGITUDINAL OSCILLATION. THE YOKE OSCILLATED LEFT AND RIGHT RAPIDLY AND WINGS WERE FLEXING 4 TO 6 INCHES, DISCONNECTED AUTOPILOT WITH NO POSITIVE AFFECT, CONDITION IMPROVED BY SLOWING DOWN THE AIRCRAFT FROM 275 TO 250-255 KTS, ACCOMPLISHED AIR TURN BACK. - VISUALLY INSPECTED BOTH WINGS, FOUND CHAFED TAPE COMING LOOSE ON THE RIGHT WING LENSE TIP. REMOVED CHAFED TAPE FROM LEFT AND RIGHT WING TIP LENSE, NO OTHER DISCREPANCIES FOUND IAW HAWKER 1000 AMM CHAPTER 20.
DURING CLIMB OUT HEARD SEVERAL RAPID POPS LASTING 3-4 SECONDS, TWO EVENTS SPACED 10-15 SEC APART. LEFT ENG N1, ITT, N2 FLUCTUATED, ALSO EXPERIENCED SOME AIRFRAME VIBRATIONS. DECLARED EMERGENCY AND ACCOMPLISHED AIR TURNBACK TO VNY. ITEM IS UNDER INVESTIGATION.
TAKEOFF ABORTED AT 75KTS FOR THE CONFIGURATION WARNING HORN THAT WAS ACCOMPANIED BY THE RED FLASHER. TROUBLESHOT SYSTEM, APPLIED POWER AND PERFORMED A COMPLETE SYSTEM OPS CHECK FOUND THE COPILOTS TRIM SWITCH WAS STICKING, CLEANED AND LUBED THE SWITCH, SYSTEM OPS CHECKED GOOD IAW HONEYWELL SPZ-8000, ARKANSAS AEROSPACE DRAWING A1-SB-005 REV B.