N728QS
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
COMPLETED A FLIGHT AND WHILE OPENING THE MAIN CABIN DOOR NOTICED HANDLE WAS LIGHLY STIFF & THEN LIGHTLY POPPED UP AND WAS WORKING. THOUGHT IT WAS PERHAPS "USER ERROR". WE THEN VERIFIED BY OPENING AND CLOSING THE DOOR A FEW TIMES TO SEE IF IT COULD BE DUPLICATED. NO ISSUES WERE NOTICED. AFTER A SECOND FLIGHT AT FLIGHT LEVEL 430 FOR OVER THREE HOURS, I ATTEMPTED TO OPEN THE MAIN CABIN DOOR. THE HANDLE WAS VERY STIFF WITH A SIGNIFICANT BIND AND THEN SUDDENLY BROKE FREE WITH A VERY LOUD BANG. THE DOOR FUNCTIONED NORMALLY DURING THE REST OF THE CYCLE. CLOSED AND OPENED THE DOOR A FEW TIMES AND HAD NO OTHER ISSUES CORRECTIVE ACTION: LOCK HOOK ADJUSTED. OPS CHECK COMPLETE. IAW CL-350 AMM 52-11-05-05.
LEFT BASE, FLAPS 20, RECEIVED AMBER AP STAB TRIM FAIL. PER QRH TURNED AUTOPILOT OFF & FLEW APPROACH TO LAND. DID HAVE TROUBLE PUSHING PLANE NOSE DOWN AFTER ADDING FLAPS 30 AND ALL THE WAY TO LANDING. PLANE HAS HAD RECENT WRITE UP FOR PRIMARY FLIGHT CONTROLS ISSUE. COULD NOT DUPLICATE. OPS CHECKED HORIZ STAB & AUTO PILOT SYS WITH NO DEFECTS. ACCOMP AMM 27-41-00-710-1!01. OPS TEST PITCH TRIM SYS. NO FAULTS. NO FAULTS ON CMC. CHECKED FAULT HISTORY FOR AP STAB TRIM FAIL FAULT NOT PRESENT. CONTACTED MANUFACTURER CRC CASE 000791327. PROVIDED DOWNLOADS OF MDC ALL REPORTS. NOTHING RECORDED RELATED ON JUNE 27TH. CRC NOTES FROM HSTECU NVM NOTHING RECORDED RELATED ON JUNE 27TH. ON TAXI OUT B3-Q06N4 FGS DIAG CODE=REPAIR 351 FGC 1200000 - PITCH, ROLL, OR YAW TRIM SYS, CRC RECOMMENDS WIRING CHECK. IAW 22-11-21-710-801. OPS TEST OF ELEV SERVO -CABLE TENSION CHK IAW AMM, FOUND INCONSISTENCIES WITH MANUAL FOR WIRING CHKS & WIRING DIAGRAM. PERFORMED SMART FIX CHKS, NO DEFECTS. PERFORMED OPS TEST OF ELEV SERVO IAW AMM 22-11-21-710, NO DEFECTS. PERFORMED ELEVR SERVO CABLE TENSIONING CHK IAW AMM 27-31--00, NO DEFECTS. ORGINAL SUBMISSION DATE: 6/30/2025.
FLT SPOILERS FAULT AMBER CAS: CLIMB INF THROUGH FL330 AT 270 KNOTS WITH THE AUTOPILOT ENGAGED, A MOMENTARY ROLL MOVEMENT OCCURRED, FOLLOWED BY A YELLOW SPOILERS FAULT, CYAN STAB TRIM FAULT CAS MESSAGES, AS WELL AS SPOILER PANELS 2&7 YELLOW ON THE FLIGHT CONTROL SYNOPTIC. SPOILER PANEL 7 ON THE RIGHT WING WAS VISUALLY OBSERVED TO BE EXTENDED APPROXIMATELY 1". SPOILER PANELS 2 AND 7 DID NOT EXTEND ON LANDING. B3-007233 CORRECTIVE ACTION; REPLACED THE SECU 1 I/A/W CL350 M/M 27-61-05 AND 27-61-00, ALL OPERATIONAL AND RIGGING CHECKS SATISFACTORY.
AT ALTITUDE, HEARD A GRINDING NOISE WHICH LASTED FOR ABOUT 5 SECONDS COMING FROM BACK OF AIRPLANE. WAS FOLLOWED WITH A LT, HYD PUMP, FAIL, CASS MESSAGE. PULLED UP SCHEMATIC & COULD SEE THE FLUID WAS DRAINING FROM LT HYDC SYS WHEN FLUID REACHED 0 GOT A AMBER LT HYDC PRESS LOW CAS MESSAGE. DECLARED AN EMERGENCY, MANUALLY EXTEND THE GEAR, PERFORMED EDHP OPERATED DRY INSPECTION CHECK, NOTED BRONZE & STEEL IN BOTH THE CASE DRAIN & PRESSURE FILTERS. REMOVED LT EDHP DUE TO SHAFT SHEARED. INSTALL NEW. PERFORMED LEAK CHECK, BLEEDING OF LT HYD SYS, NO DEFECTS NOTED. IAW AMM 29-12-01, 29-10-00 AND 12-12-00.
EMERGENCY EXIT DOORS: DURING FLIGHT THE EMERGENCY EXIT LIGHTED PYRAMID SIGN CAME OFF AND A PAX REPLACED IT UPSIDE DOWN RESOLUTION: REMOVED EMERGENCY EXIT SIGN AND FLIPPED IT UP RIGHT AND THEN RESECURED SIGN TO WALL. WORK DONE IN REF TO CL350 AMM 33-51-00
MAIN DOOR: MAIN CABIN DOOR WILL NOT CLOSE. WHEN IT GETS TO THE TOP IT SEEMS TO BIND. // SIGNOFF// DISCONNECTED CABLE AND SPERATED ACTUATOR AND CABLE REEL. FOUND CABLE REEL TO BE EXTREMELY DIRTY. CLEANED UP CABLE REEL, REATTACHED DOOR CABLE REEL AND CABLE AND PERFORMED OPERATIONAL CHECK. OPERATIONAL CHECK SATISFACTORY. REF: BOMBARDIER CL350 AMM 52-11-25.
EMERGENCY LIGHTS WILL NOT TURN OFF
AFTER SELECTING GEAR UP THE LT GEAR INDICATION SHOWED RED HASH LINES. THE ACFT DID FEEL LIKE THE GEAR WAS DOWN. NO DRAG OR PULL TO ONE SIDE. WE CYCLED THE GEAR 3X DID NOT FIX THE PROBLEM. JACKED A/C AND SWUNG GEAR SEVERAL TIMES. VERIFIED DISCREPANCY. DISCONNECTED LH MAIN LANDING GEAR DOOR. SHUT AND LATCHED DOOR MANUALLY AND CHECKED GAP OF BOTH FORWARD AND AFT PROXIMITY SWITCHES. WRUNG OUT FORWARD AND AFT PROXIMITY SWITCHES, FOUND THE AFT PROXIMITY SWITCH TO BE BAD. PROXIMITY SWITCH AND HARNESS ON ORDER, NO ETA. (BC)(DV) REMOVED AND REPLACED ALL PROXIMITY SWITCH ASSY IAW G200 MM 32-10-11. PERFORMED MULTIPLE GEAR SWING. ALL GEAR SWINGS OPS CHECK GOOD AT THIS TIME. (BC)
DURING APPROACH, SELECTED FLAPS 12 & SLATS DOWN. SLATS & KRUEGERS CAME DOWN NORMALLY BUT FLAPS DID NOT & RECEIVED A SLAT/FLAP MAINT EICAS MESSAGE. AFTER LANDING, FLAPS/SLATS AND KREUGERS ALL RECTRACTED NORMALLY. TROUBLESHOT FLAP SYS TO PDU. REMOVED FLAP PDU AND INSTALLED REPLACED PDU. PERFORMED SYS OPS CHECKS WITH NO DEFECTS NOTED AT TIME OF TEST. ALL WORK DONE IAW AMM 27-57-45, 27-51-05 AND CMP'S 275210 AND 275101. AMM REV 21.
RIGHT WINDSCREEN OUTER PANE CRACKED IN A SPIDER WEB FASHION WHILE FLYING AT FL 400. R & R RT WINDSCREEN IAW MM 56-10-05. OPS AND LEAK CHECKED GOOD.
ON PREFLIGHT, FLAPS VISUALLY APPEARED TO MOVE FREELY BUT FLAP INDICATOR HESITATED AT 12 & 20 DEGREE POSITIONS. AT 12000', STRAIGHT & LEVEL, SLATS, KRUEGERS & FLAPS ALL WORKED PROPERLY. AT 12000', LEVEL BUT TURNING, SELECTED FLAPS 12 & GOT "SLAT/FLAP MX" EICAS & NO MOVEMENT OF SLATS, KRUEGERS, OR FLAPS. RECYCLED HANDLE, & AGAIN NO MOVEMENT. ALSO TRIED SLAT BYPASS SWITCH, SAME EICAS MESSAGE BUT NO SLATS. CHECKED INTEGRITY OF WIRES ON FLAP/SLAT HANDLE. REPLACED CIRCUIT BOARDS 645 AND 82P. R & R LT AND RT NR 3 SLAT ACTUATORS IAW CMP 275227 AND CMP 275228. COMPLIED WITH FLAP/SLAT CONTROL DRIVE FUNCTIONAL TEST IAW CMP 275101 WITH NO FAULTS NOTED.
DURING CLIMB OUT COCKPIT FILLED WITH WHITE SMOKE (SMELLED AND TASTED ELECTRIC) DISCONNECTED GALLEY ELECTRIC NO CHANGE, DUMPED CABIN SMOKE, DISSIPATED TEMPORARILY THAN RETURNED. RETURNED TO DEPARTURE. FOUND LT ENGINE OVERSERVICED WITH ENGINE OIL. DRAINED ENGINE OIL TO PROPER LEVEL IAW MM 12-17-00. RAN APU AND BOTH ENGINES SEVERAL HOURS TO BURN OUT THE OIL RESIDUE FROM THE BLEED AIR DUCTS.
DURING CLIMBOUT COCKPIT FILLED WITH WHITE SMOKE (SMELLED AND TASTED ELECTRIC). DISCONNECTED GALLEY ELECTRIC, NO CHANGE. DUMPED CABIN, SMOKE DISSIPATED TEMPORARILY THEN RETURNED. FOUND LT ENG OVERSERVICED WITH ENGINE OIL. DRAINED ENGINE OIL TO PROPER LEVEL IAW MM 12-17-00. RAN APU AND BOTH ENGINES SEVERAL HOURS TO BURN OUT THE OIL RESIDUE FROM THE BLEED AIR DUCTS. AFTER ENG RUNS THE ECS SYS NO LONGER SMOKES AND THE ODOR IS AT AN ACCEPTABLE LEVEL.
ON T/O, RAISED GEAR GOT RT MAIN GEAR IN TRANSIENT LITE (BOX) INDICATION. PERFORMED FWD AND AFT UPLOCK PROXIMITY SWITCHES ADJUSTMENT AND FUNCTIONAL CHECK. FOUND BOTH FWD AND AFT SWITCHES ARE NOT WITHIN LIMIT IAW SB200-32-226. ADJUSTING SWITCHES TO WITHIN LIMIT IAW SB200-32-226. PERFORMED MLG EXTENSION AND RETRACTION OPS CHECK. CHECKED OF MLG OPS SATISFACTORY. REF SB200-32-226, G200 MM 32-30-00.
ON CLIMB OUT TOWER REPORTED RT MAIN GEAR NOT RETRACTED. INDICATIONS ON ICAS RIGHT MAINT RED BOX RED DASHES. CYCLED GEAR DOWN 3 GREEN. RETURNED TO DEPARTURE.
ON CLIMB OUT, TOWER REPORTED RT MAIN GEAR NOT RETRACTED. INDICATIONS ON ICAS RT MAINT RED BOX RED DASHES. CYCLED GEAR DOWN 3 GREEN. RETURNED TO DEPARTURE.
ON CLIMBOUT TOWER REPORTED RT MAIN GEAR NOT RETRACTED.
TAKE OFF ABORTED DUE TO RED BLEED AIR EICAS MESSAGE AND MASTER WARNING LIGHTS. UPON MOVING THRUST LEVERS TO IDLE, EICAS AND MASTER WARNING LIGHT SHUTOFF BEFORE WE WERE ABLE TO READ COMPLETE EICAS MESSAGE. LEFT APR WAS ACTIVATED AND SURGING IN RUDDER PEDDLES WAS NOTED. BOTH ENGINES TO T/O POWER. DID NOT GET A RIGHT OR LEFT BLEED AIR EICAS MESSAGE. VISALLY CHECKED BOTH ENGINES AND TAIL COMPARTMENT FOR LEAKS DURING ENGINE RUN AND NONE WERE FOUND. REMOVED EXISTING RH BLEED AIR LEAK DETECTION CONTROLLER AND INSTALELD NEW CONTROL UNIT AT LMCC DIRECTION. RAN ENGINES TO T/O POWER WITH NO FAULTS FOR ALL WORK ACCOMPLISHED RE MM 21-11-00 AND 21-61-00 ACCOMPLISHED CMP 261504 AND 210020.
DURING T/O ROLL WITH THROTTLES AT T/O DETENT THE BLEED PRESS/TEMP HIGH MSG ILLUMINATED. THE T/O WAS ABORTED. M2B- REMOVED FWD OVERTEMP SWITCH P/N 641180-1 S/N 0245 AND INSTALLED NEW FWD OVERTEMP SWITCH P/N 641180-1 S/N 0368. REMOVED AFT OVERTEMP SWITCH P/N 641180-1 S/N 9247 AND INSTALLED NEW AFT OVERTEMP SWITCH P/N 641180-1 S/N 0375. REMOVED OVERPRESSURE SWITCH P/N 642021-1 S/N 0102 AND INSTALLED NEW OVER PRESSURE SWITCH P/N 642021-1 S/N 0183. PERFORMED FUNCTIONAL AND OPERATIONAL CHECK, FUNCTIONAL AND OP'S CHECK GOOD. NO DEFECTS NOTED. ALL WORK PERFORMED IAW MM 21-11-00.
APU FIRE INDICATION ON GROUND. BLEW BOTTLE INTO APU DURING CHECKLIST. RT FIRE BOTTLE IS EMPTY. [07-12-07] REMOVED TAIL CONE AND INSPECTED APU FOR DAMAGE. FOUND NO DAMAGE. REMOVED APU FIRE DETECT LOOP AND INSTALLED A NEW GAC FURNISHED BOTTLE. PERFORMED SATISFACTORY OPS CHECKS OF THE APU AND ENGINE ARE DETECT SYS. REF G200 MM 26-10-25, 26-10-20
LEFT MAIN GEAR DID NOT RETRACT UP AND LOCK, GEAR INDICATOR SHOWED AMBER TRANSIT FOLLOWED BY A RED BOX. OBSERVED BY CONTROL TOWER TO BE DOWN. RECYCLED GEAR AND IT CAME UP NORMALLY. REMOVED L/H MLG ACUATOR & INSTALLED A REPAIRED UNIT, OPS & LEAK CHECKED GOOD IAW G200 MM CH. 32-10-20.
AFTER TAKEOFF RT MAIN GEAR INDICATOR HAD AMBER BOX, CYCLED GEAR AND WAS NORMAL BUT THEN STARTED FLASHING AMBER. RETURNED FOR LANDING WITH NORMAL GEAR INDICATION. ITEM IS UNDER INVESTIGATION.