N558QS
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
MAIN DOOR PRECATCH: WHEN OPENING THE MAIN CABIN DOOR FROM THE OUTSIDE THE DOOR WILL NOT RELEASE UNLESS THE PRECATCH IS PUSHED IN. FROM THE INSIDE THE DOOR WILL OPEN NORMALLY WITHOUT THE PRE CATCH BEING USED. SEE ATTAT HED VIDEO. CORRECTIVE ACTION; RESECURED INTERIOR PRE-CATCH HANDLE HARDWARE IAW 560XL SPM 20-10-65. OPS CHECK GOOD. NO FURTHER DEFECTS NOTED.
COCKPIT ODOR: WHILE TAXIING FOR TAKEOFF, WE SUDDENLY GOT A STRONG HOT BURNING SMELL, IT HAD AN ELECTRICAL SMELL TO IT. CORRECTIVE ACTION: PERFORMED MULTIPLE ENGINE RUNS AND APU RUNS. PERFORMED TC-5XL-21-120902MR1 (ENVIRONMENTAL CONTROL SYSTEM BLEED AND TRIM AIR DUCT BURN PROCEDURE.) THERE WERE NO ODORS OR BURNING SMELLS NOTICED DURING ANY OF THE ENGINE RUNS OR APU RUNS.
MAIN DOOR REQUIRES EXCESSIVE FORCE TO OPEN OR CLOSE LATCH. GAINED ACCESS TO MED BOLTING LINKAGE SYSTEM. FOUND PRECATCH LATCHING BOLT OUT OF ADJUSTMENT READJUSTED BOLTING SYSTEM LINKAGE. CHECKED DOOR SEVERAL TIMES FOR PROPER LATCHING AND RELEASE, OP CHECK GOOD. NO DEFECTS NOTED. RESTORED ACCESS TO MED BOLTING LINKAGE SYSTEM. WORK DONE JAW CESSNA 560XL MM 52-10-01.
MAIN DOOR PRECATCH: AFTER FLIGHT WHEN WE GO TO OPEN THE MAIN ENTRANCE DOOR. WE HAVE TO PULL THE PRECATCH HANDLE TO GET THE DOOR TO OPEN. ADJUSTED PRECATCH CABLE IMPROVE ACTUATION OF THE PRE CATCH, PRECATCH CONSISTENTLY DISENGAGES WHEN CABIN DOOR HANDLE GOES TO OPEN POSTION ALL WORK IN ACCORDANCE WITH AMM 52-10-00 THE DOOR OPS CHECK WAS GOOD.
AT ALTITUDE, GOT A FIRE BOTTLE LOW ANNUNCIATOR. CREW RAN QRH & DECLARED AN EMERGENCY. FIRE DEPART CHECKED ACFT & OBSERVED NO EVIDENCE OF FIRE. THERE ISN'T A WAY TO VERIFY WHICH FIRE BOTTLE WOULD HAVE TRIGGERED ANNUNCIATOR. FOUND NO CASS MESSAGE AT ARRIVAL TO ACFT, PERFORMED A GVI OF LT & RT ENGS FOR EVIDENCE OF HAYLON DISCHARGE. NO DEFECTS. PERFORMED GVL OF LT & RT FIRE BOTTLES & APU FIRE BOTTI.ES WITH NO DEFECTS. PERFORMED FIRE TEST, PASSED, RAN BOTH ENGS FOR 30MIN & COULD NOT DUPUCATE. HCC REQUESTED WEIGH BOTTLES TO DETERMINED IF DISCHARGED. REMOVED FWD & AFT ENG FIRE BOTTLES. FOUND AFT NR 2 BOTTLE 1 LB LESS THAN LAST HYDRO TEST. R & R AFT NR 2 FIRE BOTTLE. VISUAL CHECKED GOOD. IAW MM 26-21-01.
MAIN DOOR PRECATCH: THE PRE CATCH WILL NOT RELEASE THE MAIN CABIN DOOR. // SIGNOFF// ADJUSTED MED PRE CATCH IAW CE 560XL AMM 52-10-01. MED PRE CATCH OPERATIONAL CHECK GOOD AT THIS TIME.
EMERGENCY EXIT INTERIOR REVEAL PANEL FASTENERS RUB ON EMERGENCY EXIT DOOR SURROUND DOUBLER. FASTENERS ARE RUBBING DEEP WEAR MARKS OR HOLES IN THE STRUCTURAL DOUBLER.
RIGHT ENGINE FIRE DETECTION LIGHT: DURING CLIMB OUT FROM DAL THROUGH 12000 FT THE RH ENGINE FIRE LIGHT ILLUMINATED AND EXTINGUISHED A FEW SECONDS LATER THE LIGHT ILLUMINATED AGAIN AND EXTINGUISHED. NO ENGINE SHUT DOWN WAS REQUIRED PER CHECKLIST AND NO FIRE BOTTLE WAS USED.
MAIN DOOR: WHEN MAIN CABIN ENTRY DOOR IS OPEN, TOP HINGED STEP IS LOOSE AND MOVES WHEN STEPPED ON. DISCOVERED BROKEN HARDWARE CLIP NEXT TO STEP.
LEFT ENGINE ENGINE VIBRATION: ENGINE VIBRATION OCCURRED ABOVE 10K WHEN REDUCING POWER SETTING FROM CLIMB POWER TO CRUISE. VIBRATION CAME BACK AS WE WENT BACK TO CLIMB THEN AGAIN WHEN WE REDUCED POWER. VIBRATION ALSO OCCURRED DURING LIGHT TURBULENCE LEVEL FLIGHT CRUISE POWER. DID NOT NOTICE THE VIBRATION ON DESCENT TO LANDING. N1 DURING VIBRATION WAS HIGH 80 TO LOW 90S. ACCOMPLISHED AND SUBMITTED THE VIBE SURVEY AS REQUIRED FOR EVALUATION. PER ADDITIONAL RECOMMENDATIONS, GAINED ACCESS AND PERFORMED AN INSPECTION OF THE STARTER/GENERATOR, AC GENERATOR, AND HYDRAULIC PUMP SHAFTS WITH NO DEFECTS NOTED. DURING REMOVAL OF THE HYDRAULIC PUMP, HYDRAULIC FLUID POURED OUT OF THE CAVITY. ACCOMPLISHED A ROTATION OF THE AGB WITH NO UNUSUAL NOISES NOTED. PERFORMED ADDITIONAL AIRFRAME INSPECTIONS OF THE LEFT HAND ENGINE AND FOUND THE AFT ISOLATOR TO HAVE MOVEMENT WITHIN THE CENTER ISOLATOR BOLT AND FOUND EVIDENCE OF FLUID ON THE FWD LOWER ISOLATOR. PERFORMED A TORQUE CHECK OF THE T/R FLANGE BOLTS WITH TORQUE CHECK GOOD. DISPLACED LH ENGINE AND REMOVED THE UNSERVICEABLE UPPER FWD ISOLATOR (P/N: 9912480-1 S/N: LK2169) AND INSTALLED AN OVERHAULED UPPER FWD ISOLATOR (P/N: 9912480-1 S/N: LK2305). REMOVED THE UNSERVICEABLE LOWER FWD ISOLATOR (P/N: 9912480-1 S/N: LK1704) AND INSTALLED AN OVERHAULED LOWER FWD ISOLATOR (P/N: 9912480-1 S/N: LK2247). REMOVED THE UNSERVICEABLE AFT ISOLATOR (P/N: 9912480-2 S/N: LK0899) AND INSTALLED AN OVERHAULED AFT ISOLATOR (P/N: 9912480-2 S/N: LK0755). REMOVED THE UNSERVICEABLE LH ENGINE HYDRAULIC PUMP (P/N: 9912062-7 S/N: 0534A) AND INSTALLED AN OVERHAULED SERVICEABLE LH ENGINE HYDRAULIC PUMP (P/N: 9912062-7 S/N: 0503A). REINSTALLED ACCESS AND COMPONENTS REMOVED FOR LH ENGINE DISPLACEMENT. COMPLETED INITIAL CLOSE UP AS REQUIRED FOR RUNS. PERFORMED IDLE RUN LEAK CHECKS FOR THE LH AND RH ENGINE WITH SATISFACTORY RESULTS, FOUND 2EA WIGGINS SEAL CONNECTIONS TO BE LEAKING ON THE LH ENGINE, WITH NO ADDITIONAL LEAKS NOTED. PERFORMED HYD PUMP OPERAT
MAIN DOOR HANDLE: MAIN ENTRANCE DOOR INSIDE HANDLE BROKEN. HANDLE MOVES FREELY. REMOVED STEPS AND INSPECTED HANDLE ASSY, FOUND BOTH SCREWS ATTACHING THE HANDLE TO THE SHAFT SHEARED OFF. REMOVED FAILED FASTENERS AND REPLACED WITH NEW. REINSTALLED STEPS. DOOR HANDLE OPS CHECKS GOOD. WORK IAW CE560XL MM 52-10-01 AND 52-10-02.
EMERGENCY LIGHT OVER SEAT 7 INOPERABLE. REMOVED AND REPLACED BURNT OUT BULB, IAW CE-560XLS AMM 33-20-00, ALL CHECKS GOOD AT THIS TIME.
RIGHT ENGINE FIRE DETECTION LIGHT INTERMITTENT - IN FLIGHT AT FL280, THE R/H ENGINE FIRE WARNING LIGHT FLICKERED ON AND OFF CONTINUOUSLY FOR APPROXIMATELY FIVE MINUTES. THERE WERE NO SECONDARY INDICATIONS OF A POSSIBLE ENGINE FIRE. WING AND ENGINE ANTI ICE WERE BOTH TURNED ON DURING THIS TIME. COULD NOT DUPLICATE DISCREPANCY, ADVISED MCC OF TROUBLESHOOTING STEPS(DETAILED IN FC102) ADVISED TO CHANGE FIRE DETECTION CONTROL UNIT AND FIRE TRAY PCB AS A PRECAUTION REMOVED SUSPECTED FAULTY FIRE TRAY PCB PART# 6618003-1 SERIAL# 0726 INSTALLED INSPECTED FIRE TRAY PCB PART # 6618003-1 SERIAL # 1154 REMOVED SUSPECTED FAULTY RH ENGINE FIRE DETECTION CONTROL UNIT PART# 9912036-12 SERIAL# 0505-986 INSTALLED NEW RH ENGINE FIRE DETECTION CONTROL UNIT PART # 9912036-12 SERIAL # 1845-641 PERFORMED OPERATIONAL CHECKOUTS AS REQUIRED, CHECK GOOD. ALL WORK DONE IAW CESSNA CE-560XLS AMM AMM 26-11-00, 26-11-05-2, 26-21-00.
BOV INTERMITTENT - AT FL410, FO MADE A SLIGHT POWER INCREASE WHEN WE HEARD A FLUTTERING FOUND/POSSIBLE COMPRESSOR STALL FROM LEFT ENGINE. LEFT ENGINE ITT WENT UP AND DOWN ABOUT 100 POINTS. THE RANGE WAS BETWEEN 500 AND 600 DEGREES. THIS HAPPEN TWICE IN FLIGHT.// SIGNOFF // REMOVED THE UNSERVICEABLE LEFT HAND ENGINE TORQUE MOTOR(P/N: 30J3490-01A S/N: TRAXY000063) AND INSTALLED A NEW SERVICEABLE LEFT HAND ENGINE TORQUE MOTOR(P/N:30J3490-01A S/N: TRAXY000186). REMOVED THE ORIGINAL SECONDARY METERING PLUG(P/N: 30J1296CL34) AND INSTALLED A SERVICEABLE ORIFICE PLUG (P/N: 30J1296CL40) AND ACCOMPLISHED THE BOV OPERATIONAL CHECK IN MANUAL MODE WITH THE P10 CANNON PLUG DISCONNECTED AND INDUCED A COMPRESSOR STALL. ACCOMPLISHED AN ADDITIONAL LEFT HAND ENGINE DOWNLOAD AND SUBMITTED TO PWC FOR EVALUATION. SPOKE WITH PWC AND NO ADDITONAL FAULTS WERE NOTED AND RECOMMENDED FOR US TO CONTINUE THE RECLASSIFICATION OF THE TORQUE MOTOR.REMOVED THE SECONDARY METERING PLUG (P/N:30J1296CL40) AND INSTALLED A SERVICEABLE SECONDARY METERING PLUG (P/N: 30J1296CL44). PERFORMED AN ADDITIONAL BOV OPERATIONAL CHECK IN MANUAL MODE WITH THE P10 CANNON PLUG DISCONNECTED WITH SATISFACTORY RESULTS AND NO DUPLICATION OF A COMPRESSOR STALL. RECONNECTED THE P10 CANNON PLUG AND ACCOMPLISHED THE EEC MODE OF THE BOV OPERATIONAL CHECK WITH SATISFACTORY RESULTS. COMPLETED THE BOV OPERATIONAL CHECK WITH SATISFACTORY RESULTS. COMPLETED FOLLOW ON CHECKS AS REQUIRED FOR THE INSTALLED TORQUE MOTOR WITH SATISFACTORY RESULTS. FINAL SECONDARY METERING PLUG INSTALLED IS 30J1296CL44. ALL MAINTENANCE ACCOMPLISHED IAWPW545B EMM CH. 75-30-01, 72-00-00, 77-40-01, AND 71-00-00.
RIGHT ENGINE FIRE DETECTION LIGHT INTERMITTENT - RT ENGINE FIRE LIGHT ILLUMINATED INTERMITTENT AT CRUISE ALTITUDE. CORRECTIVE ACTION, VISUALLY INSPECTED RT ENGINE FIRE LOOP FOUND NO DEFECTS. RAN ENGINE AT VARIOUS POWER SETTINGS WITH ENGINE ANTI-ICE ON AND OFF, FOUND NO LEAKS AT THIS TIME. PER CUSTOMER REQUEST, RE-POSITIONED LT AND RT ENGINE FIRE DETECTION UNITS. ALL OPERATIONAL CHECKS GOOD.
REPAIRED CORRODED AREA ON THE LT FWD VERTICAL STABILIZER SPAR CAP, WHERE ACCESS PANEL 340ATC ATTACHES, BY BLENDING, TRIMMING SPAR WEB AND CHAMFERING THE SPAR CAP, TREATING AND PRIMING IAW FIELD REPAIR FR-560-5568-4523 REVISION (-) APPROVED BY FAA FORM 8100-9 DATED 13 SEP 2018.
THE RT ELEVATOR HAS A CRACK ON THE LOWER SKIN AT THE OUTBOARD HINGE CUTOUT. THE CRACK MEASURES APPROXIMATELY 0.25 INCHES LONG.
LEFT HORIZONTAL STABILIZER REAR SPAR CORRODED.
LEFT WING AFT SPAR SPLICE CORROSION
LEFT HORIZONTAL STABILIZER REAR SPAR CORROSION BETWEEN SS 9.3 TO SS 19.00.
PILOT SIDE PRIMARY FLIGHT DISPLAY GOT EXCESSIVELY HOT AND BURNED A HOLE IN THE IMAGE. R & R NR 1 PFD WITH NEW, REPAIRED UNIT IAW AMM 34-26-00. OPS CHECK GOOD INSPECTED CONNECTOR BEHIND PFD 1 WITH NO DEFECTS.
DURING TAXI THE ACFT PULLS HARD TO THE LT WHEN EVEN BRAKE PRESS APPLIED FROM THE RT SEAT. OPERATIONS CHECKED BRAKES & LT BRAKE FEELS SPONGY. HOOKED BRAKE BLEEDING HOSE & COMPLIED WITH BRAKE BLEEDING PROCEDURE IAW MM CH 32-44-00. REMOVED A LOT OF AIR OUT OF THE LT BRAKE. SERVICED BRAKE RESERVOIR. COMPLIED WITH TAXI CHECK & CHECKED BRAKES FROM THE PILOT & COPILOT RUDDER PEDALS. OPERATIONS CHECKED GOOD.
DURING TAXI AT SLOW SPEED RT BRAKE GRABS & PULLS ACFT TO THE RT. ALSO MAKES AN AUDIBLE NOISE. REPLACED BRAKE METERING VALVE WITH A UNIT OVH'D. OPERATIONAL CHECK AND LEAK CHECK SATISFACTORY. ALL WORK IAW CE-560XL MM CH 32-44-20.