N533QS
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
RH OVER WING EMERGENCY LIGHT DIM
UNABLE TO TRIM AIRCRAFT AFTER TAKEOFF. RECEIVED PRI STAB TRIM FAIL CAS SHORTLY AFTER. ACTIVATED SECONDARY TRIM AND WAS ABLE TO TRIM. POWERED ON THE ACFT AND VERIFED "PRI STAB TRIM FAIL" CAS HARD FAILED. REMOVED H STAB TRIM ACTUATOR AND INSTALLED A CUS SUPP OVERHUALED HSTA SATISFACTORILY PERFORMED PITCH TRIM RIGGING, STABILIZER TRIM POINTER RIGGING, AND PRIMARY STABILIZER TRIM ACTUATOR TRAVEL CHECK IAW CE-680A AMM 27-40-05 WITH NO DEFECTS NOTED. CAL TOOLING: TORQUE WRENCH TL-104160 INCLINOMETER TL-00557
DURING LANDING ROLLOUT AT ABOUT 50KTS, AIRCRAFT EXPERIENCED A TOTAL LOSS OF HYDRAULIC STEERING ACCOMPANIED BY A SEVERE NOSE GEAR CAVITATION. DURING INVESTIGATION IT WAS DISCOVERED THAT NOSE PIN HAD SHEARED FROM THE T-HANDLE INTO TWO SEPARATE PIECES. OUTER BARREL SHROUD WAS FOUND ON RUNWAY AND RECOVERED FOR FURTHER INSPECTION. DAMAGED PART IS LOCATED INSIDE THE PILOTÃâ¬â¢S CUP HOLDER FOR REVIEW. CORRECTIVE ACTION: FOUND NOSE TORQUE PIN HAD COME APART WHICH ALLOWED THE TORQUE LINK TO SEPERATE ON LANDING CAUSING THE SEVERE NOSE WHEEL SHIMMY. REMOVED AND REPLACED NOSE TORQUE LINK PIN LANYARD ASSEMBLY P/N 6742150-8 REF 680A CMM CH 32-20-01. REMOVED LH NOSE WHEEL ASSEMBLY P/N 6942060-2, S/N DO874 WITH TIRE P/N M15601, S/N 299T001 AND INSTALLED REPAIRED WHEEL ASSEMBLY P/N 6942060-2, S/N T0196 WITH TIRE P/N ML5601 S/N 436ZT247. REMOVED RH WHEEL ASSEMBLY P/N 6942060-2, S/N D0692 WITH TIRE P/N ML5601 S/N 4301T392 AND INSTALLED REPAIRED WHEEL ASSEMBLY P/N 6942060-2, S/N D0054 WITH TIRE P/N M15601 S/N5086T107 IAW 680A AMM TASK: 32-40-15. TAXI CHECK OF STEERING CHECKS GOOD.
ENG CNTRL FAULT L AMBER CAS ILLUMINATED ON TAXI IN. ACCOMPLISHED QRH PROCEDURE AND MESSAGE REMAINED. GAINED ACCESS TO AIRCRAFT, POWERED UP APU, NOTED NO FAULTS DISPLAYED. INTERROGATED CDMS, AND FOUND ALERT ID CODE1610 WITH FAULT CODE TE, WHICH IS THRUST REVERSERS. PERFORMED ENGINE RUNS FOR 20 MINUTES WITH 12 THRUST REVERSER ACTUATIONS, STILL NO FAULTS DISPLAYED, AND NO DEFECTS NOTED. ALL OPS CHECKS WERE GOOD AND MESSAGE DID NOT APPEAR AT ANY TIME AND WAS NOT LATCHED. NOTIFIED MCC OF RESULTS AND FINDINGS AND MCC ELECTED TO SIGN OFF DUE TO NO CURRENT FAULTS AND COULD NO DUPLICATE. NO FURTHER DEFECTS NOTED AT THIS TIME. ALL WORK WAS ACCOMPLISHED IN REFERENCE TO CE-680A AMM 77-00-00.
ON APPROACH RECEIVED AMBER AP STAB TRIM & RETRIM NOSE DOWN CAS MESSAGES. CREW DISCONNECTED THE AUTOPILOT AND BEGAN TO NOTICE A HEAVINESS IN THE CONTROLS. THIS CONCERNED THEM AND PROMPTED THEM TO DECLARE AN EMERGENCY WITH ATC. CREW THEN ENGAGED THE SECONDARY TRIM SYSTEM AND THE CONTROLS RETURNED TO NORMAL CORRECTIVE ACTION; REPLACED HORIZONTAL STAB LINEAR ACTUATOR IN REF TO CESSNA MODEL 680A AMM 27-40-05. RIGGING AND OPERATIONAL CHECKS SATISFACTORY. ALL WORK DONE IN REF. TO CE-680A AMM 27-40-00.
RIGHT EXTERIOR EMERG LIGHT: WING INSPECTION WILL NOT ILLUMINATE WITH THE EMERGENCY LIGHTS SELECTED ON. //SIGNOFF// - DURING INSPECTION OF EMERGENCY LIGHTING BATTERY PACK#3 , FOUND FUSE HOLDER UNTIGHT AND NOT REINSTALLED THE FUSE AND OPS CHECK GOOD IAW CE 680A AMM 33·50-06 AND AMM 33-50-06.
CABIN EMER LIGHT: EMERGENCY LIGHT UNDER SEAT 10 AND EXIT LIGHT OVER MED STAY ON. // SIGNOFF// REPLACED FORWARD #1 EMERGENCY LIGHT POWER SUPPLY. P/N OFF/ON CBS28·1 S/N OFF/ON 5568M/5132M REPLACEMENT UNIT MODIFIED BY RADIANT POWER GROUP SARASOTA FL WITH CRS W9PR345Y ON WO 3379850 17 JUNE 2022. UNIT DOM FINAL RELEASE FOR SERVICE 6/16/2022. PERFORMED SUCCESSFUL OPERATONAL CHECK OF EMERGENCY LIGHTS WITH NO DEFECTS NOTED ALL IAW CESSNA 680A AMM 33-50-06.
MAIN DOOR: "CABIN DOOR OPEN" CAS AND YELLOW LIGHT ON DOOR. AFTER ATTEMPTING TO CLOSE THE MAIN DOOR, THE YELLOW LIGHT ON DOOR STAYED ON AND "CABIN DOOR OPEN" CAS. RAN THE QRH FOR THIS TWICE AND IT DIDNT CLEAR. PERFORMED INMAL T/S. ALL SENSORS INDICATE CLOSED ON CMC WITH PAX DOOR CLOSED BUT THE CABIN DOOR OPEN CAS IS STILL PRESENT ANO OOESNT CLEAR. SENT ARES DATA TO CESSNA FOR THEIR REVIEW. WHILE WAITING ACCESS CABIN DOOR TOP STEP AND WIRING. ALL WIRING LOOKS GOOD AND BOTH SB FOR TOP STEP WJR.ING ANO INTERIOR DOOR HANDLE WIRING HAVE BEEN DONE. CESSNA CALLEO BACK, THEY ARE CONFUSED ON WHY THIS IS HAPPENING. LIKELY SUSPECT IS CABIN MON PCB NC105 ⢠THAT JS THE ONLY THING THAT MAKES SENSE OS-31-2022 = ARRIVED ONSITE. WAITED FOR PCB. REMOVED SUSPECT NCLOS ANO INSTALLED NEW PCB. NO CHANGE. TRI ED CABIN DOOR RESITS, FULL AC POWER CYCLES, BATTS DISCONNECTED, TRIED OLD PDB ANO NEW PCB 2 MORE TIMES, ALL NO LUCK. REINSTALLED ORIGINAL PCB NC105... INSPECTED WIRING GOING TO PCB CARO CAGE FOR NCLOS WITH NO DEFECTS. WAITED TO HEAR MORE FROM CESSNA. THEY ARE CONCERNED WE MAY HAVE A GARMIN PROBLEM AS THE DATA TALKS TO THE GSO ANO GE.A. WAS TOLD TO STAND BY AS CESSNA AND GARMIN WOULD BE DELIBERATING. ALL DAY ⢠NO ANSWERS FROM CESSNA EMAILS, CALLS, ETC... WHILE WAITING CHECKED MORE WIRING FOR SYSTEM, GAINED ACCESS TO PAX DOOR AGAIN, INSTALLED NEW PAX DOOR TOP STEP HARNESS WITH NO FIX. REINSTALLED ORIGINAL HARNESS, RESTORED ALL ACCESS. SWAPPED GSO 1 AND GSO L ⢠CABIN DOOR OPEN MESSAGE STILL DOESNT CLEAR. SPOKE MORE WITH MCC AND THEY GOT ERIC HOLCOMB INVOLVED WHO LOOKS AT ARES DATA AGAIN. WHAT HE FOUND WAS THAT THE S6 SWITCH FOR THE SOLENOID PAWL WAS ALWAYS CLOSED AND SO THE LOGIC OF THE DOOR WAS NEVER SATISFIED BECAUSE THE SYSTEM NEED TO SEE IT CYCLE FROM OPEN TO CLOSE IN ORDER TO CLEAR THE CAS... MCC PLACING A SOLENOID PAWL SWITCH S6 ON ORDER FOR TMW... 06·01· 2022 = ARRIVED ONSITE AND SWAPPED GSD 1 AND J BACK TO ORIGINAL POSITIONS. RESTORED ALL ACCESS.
MAIN DOOR: CABIN DOOR OPEN AMBER CAS MESSAGE DISPLAYED WITH MAIN CABIN DOOR CLOSED. COMPLETED QRH CABIN DOOR OPEN CHECKLIST CAS REMAINED ILLUMINATED. // SIGNOFF// ARRIVED ON SITE, CONNECTED BATTERIES AND APPLIED POWER TO THE AIRCRAFT. PERFORMED TWO CYCLES OF THE DOOR FROM THE EXTERIOR DOOR HANDLE. FROM THE INSIDE PERFORMED THREE CYCLES OF THE DOOR WITHOUT THE APU RUNNING. WITH THE MAIN ENTRY DOOR HANDLE DOWN AND LOCKED AN AUDIBLE LATCH IS HEARD PER NORMAL LACKING. THE MAIN ENTRY DOOR OPEN LIGHT EXTINGUISHED AND THE CABIN DOOR OPEN CAS ALSO EXTINGUISHED. ON ALL THREE CYCLES THE DISCREPANCY COULD NOT BE DUPLICATED. STARTED APU AND RAN FIVE COMPLETE CYCLES OF THE MAIN ENTRY DOOR WITH NO FAULT FOUND. THE CREW WERE STILL IN THE FBO AND I HAD THEM ALSO COME AND PERFORM MULTIPLE CYCLES. NO FAULT FOUND. I SPOKE WITH MCC AND THERE IS NO HISTORY ON THIS DISCREPANCY. MCC REQUESTED THAT I INSPECT THE WIRING HARNESS FOR ANY VISIBLE DEFECTS. I PERFORMED A GV1 OF THE MAIN ENTRY DOOR HARNESS UNDER THE TOP HINGED STEP WITH NO DEFECTS NOTED. MCC ADVISED TO CONTINUE ON WITH RELEASE. WORK COMPLETED !AW CE-680A AMM CH 52-00-00, 52-10-04.
APU STINGER HAS CORROSION ON LH AND RH SIDE UPPER SKINS. TEXTRON AVIATION ENGINEERING MEMO DQ34035M1 DATED MAR 21, 2022; 680A-0074 (N533QS) APU STINGER SIDE SKIN (CORROSION) DEEMED THE REPAIR MINOR IN SCOPE. REPAIR OF CORROSION ACCOMPLISHED PER DQ3435M1.
TAILCONE SKIN (RIGHT SIDE) DAMAGE (DRILL START). ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DQ33965M1 DATED MARCH 18, 2022; 680A-0074 (N533QS) TAILCONE SKIN (RIGHT SIDE) DAMAGE (DRILL START).
HORIZONTAL STABILIZER SKIN (LEFT UPPER/LOWER AND RIGHT LOWER) CORROSION. ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DQ33987M1 DATED MARCH 16, 2022; 680A-0074 (N533QS) HORIZONTAL STABILIZER SKIN (LEFT UPPER/LOWER AND RIGHT LOWER) CORROSION.
HORIZONTAL STABILIZER (LEFT SIDE) UPPER SPLICE STRAP CORROSION. ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DQ34003M1 DATED MARCH 16, 2022; 680A-0074 (N533QS) HORIZONTAL STABILIZER (LEFT SIDE) UPPER SPLICE STRAP CORROSION.
MAIN DOOR: WHILE ATTEMPTING TO CLOSE THE MAIN CABIN ENTRY DOOR USING THE INTERIOR DOOR CONTROL PANEL, THE MAIN CABIN DOOR LIFT MECHANISM WOULD FAIL DURING THE LIFT CYCLE AND FALL BACK DOWN TO THE FULLY OPEN POSITION. THIS OCCURRED ON SEVERAL DOOR CLOSURE ATTEMPTS. THE MAIN CABIN ENTRY DOOR WILL INTERMITTENTLY COMPLETE THE FULL LIFT CYCLE AND FULLY CLOSE. CYCLED THE MED 10 TIMES WITH NO DEFECTS NOTED AT THIS TIME. CONTACTED SITE REP FOR HISTORY. NO HISTORY AT THIS TIME. CONTACTED MCC AND TOLD THEM OF THE FINDINGS. IAW CE680A AMM MED TROUBLE SHOOTING 52-00-00.
CLIMBING THROUGH 4000FT RECEIVED A FUEL FILTER BYPASS R CAS MESSAGE. RAN CHECK LIST AND LANDED 900 POUNDS OVERWEIGHT WITHOUT INCIDENT. **** CORRECTIVE ACTION **** REMOVED FUEL FILTER HOUSING AND FOUND A LIGHT AMOUNT OF DEBRIS IN FILTER. CONTACTED MCC & PRATT & WHITNEY FLUSHED HOUSING, INSTALLED NEW FILTER. REMOVED AND REPLACED IMPENDING BYPASS SWITCH. SUMPED FUEL TANKS NO DEBRIS WAS NOTED. RAN ENGINE FOR 30 MINUTES SHUTDOWN. REMOVED AND INSPECTED NEW FUEL FILTER FOR DEBRIS. NO DEBRIS WAS NOTED IN FUEL FILTER OR HOUSING. REINSTALLED FUEL FILTER & HOUSING WITH NEW PACKING. LEAK AND OPS CHECKS OF FILTER AND IMPENDING BYPASS SWITCH GOOD. WORK DONE IAW PW 306D1 MM 72-00-00, 73-10-03.
DURING FLIGHT AT FL400 GOT A SEVERE UNKNOWN AIRFRAME VIBRATION. THE VIBRATION WAS FELT THROUGHOUT THE ENTIRE AIRCRAFT. THERE WERE NO ASSOCIATED CAS MESSAGES, NO UNSAVED GEAR INDICATIONS, NO SPOILER DEPLOYED INDICATIONS. THE AIRCRAFT DID NOT LAND OVER WEIGHT. POST FLIGHTED AIRCRAFT ONLY FOUND THE RIGHT NOSE GEAR DOOR SLIGHTLY LOOSER THAN THE LEFT. CREW FOLLOWED ALL KNOWN COMPANY PROCEDURES. INSPECTED THE FUSELAGE AND NO LOOSE PANELS WERE FOUND. INSPECTED THE WINGS AND FOUND THE LEFT WING #4 SPOILER PANEL WAS VIBRATING WHILE TAPPING ON IT AND ALSO NOTED THE INBOARD AFT CORNER WAS NOT FLUSH WITH THE #5 PANEL NEXT TO IT. THE FLAP COVE WERE THE TRAILING EDGE RESTS ON A SUPPORT, THERE IS GAP BETWEEN THE PANEL AND THE SUPPORT. THE INBOARD HINGE ON PANEL #4, OUTBOARD HINGE ON PANEL #5 AND THE INBOARD HINGE ON PANEL #3 DOES TO HAVE SOME FREE PLAY. JACKED THE AIRCRAFT. WITH THE LANDING GEAR UP AND STOWED, CHECKED THE LANDING GEAR DOORS FOR SECURITY, BOTH MAIN GEAR DOORS HAVE SOME FREE PLAY. ADJUSTED BOTH MAIN GEAR DOORS. SWUNG LANDING GEAR DOOR ARE TIGHTER AGAINST THE WINGS. DOWN JACKED AIRCRAFT. REMOVED SPOILER SPEED BRAKE PANELS #3, #4 AND #5. ON PANEL #3, REMOVED AND REPLACED 3 BOLTS AND 2 BUSHINGS. ON PANEL #4, REMOVED AND REPLACED 5 BOLTS AND 2 BUSHINGS. ON PANEL #5, REMOVED AND REPLACED 3 BOLTS AND 2 BUSHINGS. RE-INSTALLED ALL 3 PANELS. OPS AND TRAVEL CHECKS GOOD, NO MORE FREE-PLAY IS NOTED.
DURING CRUISE FLIGHT, AT 11000 FEET, WITH APU OFF , THERE WAS A FOUL MUSTY ODOR FROM THE ACM. REMOVED AND REPLACED THE THE FILTERS, OPS CHECKED GOOD IAW MM 21-70-10.
OVERTEMP NR 2 ENGINE ON TAKEOFF, TEMPERATURE WENT TO 797 DEGREES FOR 2 SECONDS. ABORTED TAKEOFF. ITEM IS UNDER INVESTIGATION.
AIRCRAFT WAS SQUAWKED WITH NR 1 ALTERNATOR DROPPING OFF IN FLIGHT. DURING TROUBLESHOOTING THE TECHNICIAN FOUND SMOKE TRAILS ON THE GG PANEL. LOCATED ON THE AFT SIDE OF THE REAR FACE OF THE PRESSURE BULKHEAD. A MORE CLOSE INSPECTION REVEALED A DESTROYED FUSE HOLDER WITH ACCOMPANING WIRE DAMAGE, GCU AND LINE CONTACTOR DAMAGE, AND A HOLE BURNED THROUGH THE GG PANEL ITSELF AT THE FUSE HOLDER LOCATION. THE DAMAGE WAS CENTERED UNDER THE LEFT SIDE OF THE FUSE BLOCK WHICH HAD DESINTERGRATED. IT WAS UNDETERMINED AS TO WHICH COMPONENT INITIATED THE DAMAGE. (EA17200504804)
AIRCRAFT WAS SQUAWKED WITH NR 1 ALTERNATOR DROPPING OFF IN FLIGHT. DURING TROUBLESHOOTING THE TECHNICIAN FOUND SMOKE TRAILS ON THE (GG PANEL), LOCATED ON THE AFT SIDE OF THE REAR FACE OF THE PRESSURE BULKHEAD. A MORE CLOSE INSPECTION REVEALED A DESTROYED FUSE HOLDER, WITH ACCOMPANYING WIRE DAMAGE, GCU AND LINE CONTACTOR DAMAGE. THERE WAS A HOLE BURNED THROUGH THE (GG PANEL) ITSELF AT THE FUSE HOLDER LOCATION. THE DAMAGE WAS CENTERED UNDER THE LT SIDE OF THE FUSE BLOCK, WHICH HAD DESINTEGRATED. IT WAS UNDETERMINED AS TO WHICH COMPONENT INITIATED THE DAMAGE. (EA17200504804)
ON SHORT FINAL WITH A REDUCTION IN POWER NR 2 ENG FAILED AND MASTER CAUTION ILLUMINATED. OIL PRESSURE CAUTION LIGHT CAME ON NOTICED OIL PRESSURE GAUGE READ 10 PSI, ENGINE SHUTDOWN UNCOMMANDED. - REMOVED RT THROTTLE RDVT AND INSTALLED A NEW RDVT AND RIGGED IAW HAWKER 1000 MM CHAPTER 76-10-00 USING THRUST LEVER TEST SET. ACCOMPLISHED SATISFACTORY ENGINE OPERATIONAL GROUND CHECK IAW HAWKER 1000 MM CHAPTER 71-00-00.
THE AIRCRAFT WAS DETERMINED TO HAVE LEAKING THERMAL RELIEF VALVE. ORDERED REPLACEMENT PART. RECEIVED 4 EACH NEW RELIEF VALVES. ALL 4 EACH LEAKED. SUBMITTER SUSPECTS SPRING IS WEAK OR POOR FIT OF PISTON.
FOUND DURING PRE-FLIGHT. APU HOSE (FUEL FEED) WAS BURNED THROUGH THE PLASTIC SHIELD. THE FIRE RETARDANT COATING HAD NOT BEEN DAMAGED. CAUSE: HOSE LOCATED TOO CLOSE TO HOT AIR LINE. FIX: ROUTE LINE IN NEW POSITION.