N206QS
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
WHILE CLIMBING THROUGH FL370 WE RECEIVED FLAP OVER SPEED CLACKER WITH ASSOCIATED VMO LIMIT MESSAGE ON ATS. FLAP AND GEAR INDICATIONS APPEARED ON MFD, BUT FLAPS WERE STILL AT 0. COMPLIED WITH QRC & QRH PROCEDURES. FLAP & GEAR INDICATIONS APPEARED & DISAPPEARED MULTIPLE TIMES DURING FLIGHT. ONE INSTANCE FLAP SHOWED 2 FOR A SPLIT SECD & RETURNED BACK TO ZERO. NO CONTROL ABNORMALITIES WERE NOTED DURING FLT AT ANY TIME. PERFORMED FLAP OPS CHKS, NO ANOMALIES IAW AMM 27-54-00. CRC REPLIED TO INSPECT RT FLAP POSITION TRANSMITTER & WIRING. FOUND FLAP POSITION RAW DATA READING .9 DEG. WITH FLAPS AT ZERO. R & R RT FLAP TRANSMITTER IAW AMM 27-55-01, PERFORMED RIGGING & OPS CHKS IAW AMM 27-55-01, OPS CHKD GOOD.
WHEN SECURING THE AIRCRAFT WE ARE UNABLE TO LATCH THE DOOR SHUT FROM THE OUTSIDE. THE PUSH BUTTON ON THE HANDLE WILL NOT LATCH SHUT. A PICTURE OF THE HANDLE AND PUSH BUTTON NOT LATCHING WILL BE ATTACHED. WE ARE ABLE TO SHUT THE DOOR AND LATCH IT SHUT FROM THE INSIDE. WE WILL HAVE TO EXIT THE AIRCRAFT FROM THE CARGO DOOR. ANYONE ENTERING THE AIRCRAFT WILL HAVE TO ENTER FROM THE CARGO DOOR. CORRECTIVE ACTION: REMOVED MAIN ENTRY DOOR EXTERIOR HANDLE KEY LOCK ASSY AND INSTALLED NEW LOCK ASSY. ADJUSTED KEY LOCK ASSY FOR SMOOTH LOCKING AND LATCHING OPERATION. MX PERFORMED IAW CL-650 AMM 52-11-07 & 52-73-01
UPON APPROACH WE RECEIVED AMBER FLAPS FAIL CAS. RAN APPROPRIATE CHECKLIST AND LANDED. LANDING WAS UNEVENTFUL. PERFORMED MULTIPLE SUCCESSFUL OPS CHECKS OF THE FLAPS AS REQUIRED. COULD NOT DUPLICATE FAULT AT THIS TIME. WORK DONE IN REFERENCE TO AMM 27-53-04.
ON APPROACH INTO KMMU, FLAPS 20 CALLED FOR AT APPROX. 200 KTS. FLAPS FAIL AMBER CAS MESSAGE ILLUMINATED AND FLAPS INDICATED 0. FLAP FAIL APPROACH AND FLAP FAIL LANDING QRC COMPLETED AND ZERO FLAP LANDING ACCOMPLISHED AT EWR. APPLIED APU POWER TO AIRCRAFT. PERFORMED MULTIPLE FLAP SYSTEM OPERATIONAL CHECKS AND FLAPS OPERATED NORMALLY. PER 650 FLAPS FAIL T/S GUIDE SCENARIO 2, PERFORMED FCU POWER AND GROUND VERIFICATION CHECKS. NO FAULTS NOTED. FURTHER T/S OF SYSTEM REQUIRES FLAP SYS BREAKOUT BOX SCHEDULE TO DELIVER 4/22 @ 2400. W.O. 4/21/25 PERFORMED ALL TS REQUIRED FOR FLAP SYSTEM PER TS GUIDE SCENARIO 2. NO DEFECTS NOTED AT THIS TIME. FLAP SYSTEM OPERATION NORMAL. CONTACTED MCC WITH FINDINGS. MCC/ FSR ADVISED TO PERFORM BDU OEPRATING TEMPERATURE VARIATION PROCEDURE. SOURCED FREEZE SPRAY LOCALLY TO PERFORM CHECKS. W.O. 4/22/25. GAINED ACCESS TO LH AND RH BUDS. PERFORMED TS AS SUGGESTED WITH NO DEFECTS NOTED. PERFORMED GVI OF FCH. NO DEFECTS NOTED. PERFORMED ETENTION CHECK OF PINS AT CONNECTOR FOR FCH AND FCU. NO DEFECTS NOTED. MANIPULATED WIRING AT FCH WHILE OPERATING FLAPS THROUGH THE FULL RANGE OF MOVEMENT. NO DEFECTS NOTED. CONTACTED MCC WITH FINDINGS. DUE TO THE EXTENSIVE HISTORY OF THIS DISCREPANCY, WE WERE ADVISED TO STAND BY WHILE MCC/FSR DISCUSSES AND DETERMINES THE NEXT COURSE OF ACTION. W.O. 4/23/25. PERFORMED LH/RH BDU SIG1 AND SIG2 SIGNAL READINGS WITH BOB AND SENT TO MCC/FSR FOR REVIEW. PER MCC AIRCRAFT ON HOLD. WAITING ON BOMBARDIER/MCC FOR NEXT COURSE OF ACTION. W.O. 4/24/25 PER MCC AND FLT. TACTICAL MANAGER. PERFORMED FINAL OPS CHECKS AND ALL OPS CHECKS ARE GOOD. NO DEFECTS NOTED AT THIS TIME. RESTORED ALL ACCESS REQUIRED FOR MX. WORK PERFORMED IAW AMM 27-50-00. LH/RH BDUS ACCESS PANELS REQUIRE CURE CHECK. CURE CHECK GOOD. ORIGINAL SUBMISSION DATE: 4-24-2025
STANDBY EMERGENCY POWER: DEPLOYMENT ADG ABOVE 18000 CORRECTIVE ACTION; PERFORMED GVI OF ADG STRUCTURE AND DOOR DUE TO DEPLOYMENT WITH NO DISCREPANCIES NOTED. STOWED ADG IAW CL-650 AMM 24-23-01-840-807. SWAPPED GCU 1 & GCU 2. RAN ENGINES FOR OPERATIONAL TEST, ALL CHECKED GOOD.
FLAPS FAIL AMBER CAS: FLAPS WERE AT 20 ON APPROACH AND WHEN FLAPS WERE SELECTED TO 30 THEY STAYED IN THE 20 POSITION ANDWE GOT THE FLAPS FAIL CAS MESSAGE. CORRECTIVE ACTION; REPLACED FLAP CONTROL UNIT, LT & RT INBD FLAP OUTER ACTUATORS, LT & RT OUTBD FLAP INBD ACTUATORS AND ALL LT & RT FLAP FLEXIBLE DRIVE SHAFTS. PERFORMED SYSTEM RIGGING AND REQUIRED OPS CHECKS. WORK PERFORMED IAW CL 650 AMM 27-52-01, 27-53-04, 27-53-07 & 27-51-01.
THE MAIN CABIN DOOR LATCH WILL NOT POP OPEN, SO WE CAN TURN IT AND OPEN THE MAIN CABIN DOOR FROM THE OUTSIDE. THE DOOR LATCH WAS UNLOCKED. WE PUSHED THE RELEASE BUTTON. NOTHING HAPPENED. THE HANDLE IS STUCK IN ITS STOWED POSITION. THEREFORE, THE DOOR CANNOT BE OPENED FROM THE OUTSIDE. ///CORRECTIVE ACTION/// ARRIVED AT THE AIRCRAFT AND ATTEMPTED TO OPEN THE MAIN ENTRY DOOR. THE DOOR HANDLE WOULD NOT SPRING OUT AFTER HITTING THE PUSH TRIGGER BUTTON. AFTER MULTIPLE ATTEMPTS THE HANDLE SPRUNG OUT. FOUND THAT THERE WAS A LACK OF LUBRICATION CAUSING THE HANDLE LATCH TO GET STUCK CLOSED. CLEANED ALL VISIBLE SURFACES AND APPLIED LUBRICATION AS NEEDED. DOOR HANDLE OPEN AND CLOSES WITHOUT ANY DEFECTS. OP CHECKS GOOD. WORK PERFORMED IN REF TO CL-650 AMM 52-11-07.
LIFTING OFF OUT OF KVNY & CHANGING THE DECK ANGLE, GOT TAIL TANK HVY CAS & TAIL XFER SOV CLSD CAS ILLUMINATED. FUEL APPEARED TO BE DRAINING INTO TAIL TANK. REACHED 1900 LBS. LEVELED OFF AT 6000 & PROCEEDED WITH CHECKLIST & INTIALLY PRIMARY XFER FOR TAIL TANK WAS WORKING. DUMPED FUEL OUT OF TAIL TANK & SEVERAL MIN LATER GOT PRI TAIL XFER CAS. GOT AUX TANK HEAVY CAS & SWITCHED TO THE SEC XFER PUMP. SEVERAL MIN AFTER THAT THE SEC TAIL XFER CAS & THIS LEAD US OUTSIDE OF OUR CHECKLIST AND WE THEN OVERWEIGHT LANDED IN KLAX. REPLACED FUELS SYS COMPUTER WITH A REPAIRED UNIT IAW AMM 2841-13-000/4000-801 & PERFORMED A SATIS SELF TEST IAW AMM 28-41-13-740-801, INSTALLED FLOW SWITCH ASSY IAW AMM 28-15-19-400-801
CABIN DOOR OPEN CAS: ERRORNOUS PAX DOOR OUT MESSAGE IN CRUISE FLIGHT, WENT OUT BASE LEG. ERFORMED CLEANING OF THE INTERIOR DOOR ANDLE RELEASE SWITCH AND MODEL 700 MAINTENANCE MANUAL (REV 9) 52-10-00 (ORIGINAL ISSUE) CABIN DOOR - ADJUSTMENT/TEST, THEN PERFOMRED CABIN DOOR LATCH/LOC SYSTEM - ADJUSTMENT/TEST. OPERATIONAL TEST FOUND GOOD NO FURTHER DEFECTS NOTED
DURING TAXI FEELS LIKE THE BRAKES DRAGGING. TAKES AN ABNORMAL AMOUNT OF THRUST TO MAINTAIN TAXI SPEED. BRAKE PEDALS HAVE ABOUT AN INCH OF FREE PLAY BEFORE FEELING FIRM. WITH ALL HYDS OFF & PRESSURE BLEED OFF BY CYCLING BRAKES & FLT CONTROLS, BRAKE PEDALS CAME BACK TO NORMAL WITH LITTLE TO NO FREE PLAY. POST FLT INBD BRAKE CALIPERS WARM, OTBDS COOL WITH BREAKS OFF AFTER BLOCK IN. ON TAXI IN, CYCLED ANTI-SKID OFF, NO DIFFERENCE. TURNED ANTI SKID ON & A MOMENTARY ACCELERATION, THEN BRAKES GRABBED. REMOVED NLG SELECTOR VALVE, DUE TO BRAKE PRESSURE HOLDING AFTER BRAKE RELEASE, & REPLACED. SYS BLED & FUNCTIONAL CHKD, NO DEFECTS, SYS LEAK & OPS CHKD GOOD. WORK PERFORMED IAW AMM 32-33-13. ORIG SUB DATE: 1/24/2023
FOUND DAMAGE TO THE INSIDE MED AFTER CABIN PREP BY OUR SERVICE HUB TEAM. DAMAGE IS 2" X 2.8" IMPACT DAMAGE WAS REPAIRED IAW AQRD EWO-3717 REV IR.
MAIN DOOR MOTOR: MAIN DOOR MOTOR SEEMS TO BE JAMMED AND CABLE BOUND INSIDE MOTOR. DOOR IS PARTIALLY STUCK OPEN. HAVE TO EXIT THROUGH BAGGAGE DOOR. SEE ATTACHED PHOTO. // SIGNOFF // AFTER VISUAL INSPECTION WE FOUND THE DOOR CABLE HAD COME OFF THE MED MOTOR PULLEY INSIDE THE DOOR. WE SUPPORTED THE DOOR AND REMOVED THE MED CABLE FROM THE AIRFRAME AND GAINED ACCESS AS REQUIRED FOR THE DOOR MOTOR. WE FOUND THE DOOR CABLE BOUND UP AROUND THE MED MOTOR SHAFT WITH SEVERAL KINKS AND BROKEN STRANDS. WE THEN REMOVED THE SERVICEABLE MED MOTOR FOR INSPECTION OF DAMAGE AND FOUND ONLY THE CABLE NEEDING TO BE REPLACED. REMOVED DAMAGED CABLE PN:2R49573001-1 SN: N/A AND REPLACED WITH A NEW CONDITION CABLE PN:2R49573001-1 SN: N/A IAW CL650 AMM 52- 11-22 ON THE BENCH THEN INSTALLED THE EXISTING SERVICEABLE DOOR MOTOR AND ROUTED THE CABLE IAW CL650 AMM 52-11-19. PERFORMED DOOR OPERATIONAL CHECKS IAW CL650 AMM 52-11-19 AND NO DEFECTS WERE NOTED.
EMERG EXIT SIGN/LIGHT: AT THE MAIN CABIN DOOR, THERE ARE TWO EMERGENCY EXIT SIGNS-- ONE ON THE CEILING ABOVE THE DOOR AND ONE AT THE FORWARD BASE OF THE DOOR-- NEITHER ONE LIGHTS UP WHEN THE EMERGENCY LIGHT SWITCH IS TURNED ON.///SIGN-OFF///REMOVED AND REPLACED MAIN ENTRY EMERGENCY EXIT LIGHT POWER SUPPLY IAW CL-650AMM 33-51-01-000-801. OPS CHECK GOOD.
LEFT ENGINE ENGINE VIBRATION INDICATION ILLUMINATED - DURING CLIMB OUT LEFT ENGINE FAN VIB TURNED AMBER AND READ 3.1. AT 8000 FEET AND CLIMBING WE HAD TO CONTINUE TO REDUCE POWER TO KEEP VIB IN THE GREEN. A LIGHT VIBRATION COULD BE FELT THROUGH OUT THE AIRCRAFT. WE DESCENDED TO 7000 FEET WHERE THE POWER WAS SET AT 72.2 %N1 AND 600 ITT THE VIB READ 2.6. ON THE GROUND AT IDLE THE VIB READ .7 AND N1 WAS 24.4 N2 WAS 63.1 AND ITT WAS 514. // SIGNOFF // USING THE HIGH VIBRATION CAUSED BY FAN TROUBLE SHOOTING SHEET FOUND FAN BLADES TO SHOW NO SIGNS OF DAMAGE AND WERE LIKELY NOT THE CAUSE OF THE INDICATION.REF CF34B SERVICE MANUAL SEL-780 REV 60 CH 72-00-00. PER GE FRS SWAP THE ACCELEROMETERS AND PERFORM AND ENGINE RUN SWAPPED THE LH AND RH ENGINE VIBRATION ACCELEROMETERS. REF CH 650 AMM 77-31-01-000-801/400-801. PERFORMED THE SELF-TEST OF THE ENGINE VIBRATION MONITORING SYSTEM AND ENGINE RUNS AND FOUND THAT AFTER ENGINES STABILIZED AT IDLE THE LH WAS READING .5 AND THE RH WAS 0 0 FLICKERING TO 0.1 AFTER 10 MINUTES THE LH ENGINE DROPPED TO 4 AND THE RH READ 0 REF CH 650 AMM 77-31-00-740-801 REMOVED AND REPLACED THE EVM SIGNAL GENERATOR WITH A REPAIRED UNIT REF CH 650 AMM 77-31-00-740-801. PERFORMED THE SELF-TEST OF THE ENGINE VIBRATION MONITORING SYSTEM AND ENGINE RUNS AND FOUND THE LH SIDE WAS .4 ON STARTUP BUT AFTER 10 MINUTES IT DROPPED TO .2. THE RH SIDE STARTED AT .3 AND AFTER 10 MINUTES WAS FLICKERING BETWEEN .2 AND 3 REF CH 650 AMM 77-31-04-400-801 ALL READINGS ARE WITHIN LIMITS AT THIS TIME. NO FURTHER DEFECTS NOTED. TORQUE WRENCH ID: TUSJ1982 DUE· 9-23-2020 METER ID:TUSJ1977 DUE: 5-20-20
GEAR HAD TO BE MANUALLY EXTENDED, AFTER DOING A OCF FOR THE AIR DRIVEN GENERATOR DROP. SWUNG GEAR IAW CL650 AMM 32-303-00 REV 5. NO DEFECTS NOTED.
CABIN LT MOST FWD REAR FACING SEAT, NR 3 SIDE LEDGE OUTLET REPLACED DUE TO I-PAD CHARGER ARCING. R & R THE CABIN SIXTY-HERTZ OUTLET AT THE LT FWD ARM LEDGE STORAGE BOX AND OPS CHECKS GOOD IAW THE ACFT SUP MM 24-25-05. INSTALLED, PN: R4T-BLACK. UPON FURTHER REVIEW, THE I-PAD CHARGER WAS NOT FAULTY. IT APPEARS THAT THE CHILD SAFETY SHUDDER PREVENTED OR CAUSED THE PLUG FROM BEING INSERTED IN A NORMAL WAY. A 45-DEGREE APPLICATION TO THE PLUG HAD TO HAVE OCCURRED WHICH ALLOWED THE PLUG PRONGS TO CONTACT THE SUPPORT BAR THAT WAS PARTIALLY THROUGH THE OUTLET OUTER PLASTIC CASE.
WHILE ACFT IN CONFORMITY INSPECTION NJS & CMH, FLIGHT OPERATIONS TRAINING IN CABIN PLUGGED IN AN ONBOARD TABLET CHARGER TO A CABIN OUTLET, 110V A/C & OBSERVED ARCING & QUICKLY REMOVED FROM OUTLET. NOTHING FURTHER HAPPENED. OBSERVED TABLET CHARGER PLUG BLADES WITH HEAT DAMAGE. MX HAS BEEN DIRECTED TO REPLACE 110V A/C CABIN OUTLET & TABLET CHARGER. INSTRUCTED CMH RS TO CAPTURE EFFECTED COMPONENTS FOR POSSIBLE INVESTIGATION. REMOVED OUTLET IAW MM 24-25-05. INSTALLED THE CABIN SIXTY-HERTZ OUTLET AT THE LEFT FORWARD ARM LEDGE STORAGE BOX AND OPS CHECKS GOOD IAW THE SUPPLEMENTAL MAINTENANCE MANUAL 24-25-05.