N743QS
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 |
| NETJETS AVIATION, INC. (DXTA) | Operator | 2021-11-21 – 2021-11-21 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
MAIN PASSENGER DOOR RAILING STUCK IN THE UP POSITION. DOOR CAN'T CLOSE. REMOVED DAMAGED HANDRAIL (P/N 1005210201-001 S/N E12) AND HANDRAIL FITTING. INSTALLED NEW CUSTOMER SUPPLIED HANDRAIL (P/N 1005210201-001 S/N T2PL6D00DKNBV) AND HANDRAIL FITTING. WORK PERFORMED IAW CL-350 AMM 52-11-27.
AFTER LANDING AND SHUTTING DOWN REGARDLESS OF THE EMERGENCY LIGHT SWITCH POSITION THE RED EMERGENCY LIGHT UNDER SEAT 4R STAYS ON. UPON INITIAL POWER UP WE WERE UNABLE TO DUPLICATE FAULT. DURING OP CHECK OF EMERGENCY LIGHTS FOUND SEAT 4R TO FAIL TEST. AFTER FURTHER TROUBLESHOOTING FOUND THE CONNECTIONS FOR THE ACCENT LIGHTING AND EMERGENCY LIGHTING TO BE INCORRECT. CORRECTED CONNECTIONS AND CONFIRMED CORRECT CONFIGURATION AS REQUIRED IN REF. TO SEAT ACCENT LIGHT WIRING DIAGRAM AND ALL IS WORKING AS ADVERTISED AT THIS TIME. PERFORMED OPS CHECK OF THE EMERGENCY LIGHT SYSTEM IAW AMM 33-50-00. OPS CHECKED GOOD AT THIS TIME.
DURING A FUSELAGE EXTERIOR INSPECTION FOUND CORROSION AND THE SUPPORT ANGLE BELOW THE AFT ENTRY DOOR THRESHOLD AROUND THE FASTENER NUTPLATES.
MAIN DOOR: MAIN DOOR OPENED NORMALLY BUT ON 3RD ENTRY THE DOOR DROPPED SEVERAL INCHES. SOMETHING GAVE WAY AND THE DOOR WILL NOT TAKE WEIGHT WITHOUT MAKING CONTACT WITH THE FUSELAGE. THE DOOR WILL NOT CLOSE PROPERLY. MAIN DOOR BEARINGS AND INTERNAL LOCKING POINTS CLEANED AND LUBRICATED IAW AMM 12-22-00. DOOR OPS CHECKED MULTIPLE TIMES AFTER LUBRICATION AND CLEANING WITHOUT FAULT. OPS CHECK GOOD AT THIS TIME.
MAIN HYDRAULICS: UPON INTIAL TAXI OUT, AMBER "OUTBD BRAKES FAIL" ILLUMINATED. RAN APPROPRIATE CHECKLIST. NO CHANGE. B3-007113 // SIGNOFF// PULLED AND RESET CB: RCBP-C15 AND PERFORMED THE HARDWARE MONITOR TEST, PERFORMED THE BCU EPROM AND THE BCV RESISTANCE TEST, ALL TESTS PASSED. NO BRAKE SYETEM CAS MESSAGES OBSERVED. ALL 1B AND OB BRAKE SYSTEM PRESSURES AT NORMAL. WORK PERFORMED IAW CL-350S AMM 45-45-01-970-802, 32-43-00. NO FURTHER DEFECTS NOTED.
IFIS: PILOTS SIDE PFD FAILED, BLACK SCREEN. COPILOTS PFD HAD RAW DATA ONLY. AMBER PDF X TALK FAIL ILLUMINATED. AMBER EFIS MISCOMPARE ILLUMINATED AUTO PILOT AND FLIGHT DIRECTOR FAILED. FOLLOWED CHECKLIST. // SIGNOFF// ACCESSED AIRCRAFT AND APPLIED EXTERNAL POWER. PILOT'S PFD POWERED UP WITH NO DISCREPANCIES BEING NOTED AT THIS TIME. AMBER PDF X-TALK FAIL & AMBER EFIS MISCOMPARE WERE NOT VISIBLE ON THE CAS MESSAGES. PERFORMED OPERATIONAL TEST OF THE ADAPTIVE FLIGHT- DISPLAY UNITS PER BOMBARDIER CHALLENGER 350 AMM 31-61-01. NO DISCREPANCIES WERE NOTED AT HIS TIME. ALL CHECKS WERE GOOD. UNDER ADVISEMENT OF NEUETS MCC WE WILL SWAP NO.1 ADAPTIVE FLIGHT- DISPLAY UNITS WITH NO.3 AND REPERFORM OPERATIONAL TEST OF THE ADAPTIVE FLIGHT-DISPLAY UNITS FOR MAINTENANCE CONVENIENCE. REMOVED SERVICEABLE NO. 1 ADAPTIVE FLIGHT-DISPLAY UNIT PN: 822-1917-328, SN: 4865KN AND INSTALLED IN THE NO. 3 POSITION. REMOVED SERVICEABLE NO. 3 ADAPTIVE FLIGHT- DISPLAY UNIT PN: 822-1917-328, SN: 48658C AND INSTALLED IN THE NO. 1 POSITION. ALL WORK PERFORMED PER BOMBARDIER CHALLENGER 350 AMM 31-61-01. REPERFORMED OPERATIONAL TEST OF THE ADAPTIVE FLIGHT- DISPLAY UNITS PER BOMBARDIER CHALLENGER 350 AMM 31-61-01 WITH NO DISCREPANCIES BEING NOTED AT HIS TIME. ALL CHECKS WERE GOOD. NO FURTHER ACTION REQUIRED AT THIS TIME.
ENROUTE, A PASSENGER GOT STUCK IN THE LAV AND COULD NOT RELEASE THE LOCK. WE TRIED MULTIPLE OPTIONS, CALLED MAINTENANCE, AND TRIED MORE OPTIONS. WITH NO AVAIL TO OPEN DOOR, WE WERE INSTRUCTED BY MANAGEMENT TO BREAK DOOR TO GET THE PASSENGER FREE. WE KICKED IN THE DOOR, REMOVING IT FROM THE HINGES AND PLACED IN CARGO COMPARTMENT. SIGNOFF, RECEIVED LAV FOOTER PANEL AND STAINED TO MATCH LAV DOOR, IAW GETI 4000 REV 1. REINSTALLED PANEL INTO AIRCRAFT LAV DOOR AND REINSTALLED LAV DOOR INTO AIRCRAFT, IAW HC206955000-SMM-2 REV 2 CH NR 25-23-01.
PRI STAB TRIM FAIL AMBER CAS ILLUMINATED - WITH GEAR DOWN SELECTED FLAPS 10 WHILE DESCENDING. GOT AP HOLDING NOSE UP CAS AND AP STAB TRIM FAIL CAS MESSAGES. RAN QRH FOR AP STAB TRIM FAIL AND THEN GOT PRI STAB TRIM FAIL CAS MESSAGE. RAN QRH GOT SECONDARY TRIM BACK EXITED QRH STEP 4. B3-006872. //SIGN-OFF// REMOVED OLD HSTECU AND INSTALLED A CUSTOMER SUPPLIED REPAIRED UNIT. ALL CHECKS GOOD. ALL WORK DONE IAW AMM CH. 27-41-21. OLD HSTECU P/N C47329-012 S/N 642 REPAIRED HSTECU P/N C47329-012 S/N 051 STEP 1: PERFORMED NVM DOWNLOAD OF SECU 1 AND SECU2 AS WELL AS NVM DOWNLOAD OF HSTECU AND MDC FAULT HISTORY DOWNLOAD AND EMAILED TO MCC AND NJA REP. ITEMS IN REVIEW. PER REP, REPLACE THE HSTECU. STEP 2: RECEIVED HSTECU FROM FBO. CHECKED PART AGAINST SUPPLIED PAPERWORK, PART CHECKS GOOD. RETURNED TO AIRCRAFT. REMOVED OLD HSTECU AND INSTALLED A CUSTOMER SUPPLIED REPAIRED UNIT. POWERED ON AIRCRAFT AND PERFORMED ADJUSTMENT/TEST OF THE HSTECU WHICH INCLUDES OPS TEST OF THE RUDDER TRAVEL LIMITER ACTUATOR 27-21-28-710-801, ELECTRICAL RIGGING OF THE RUDDERTRAVEL LIMITER ACTUATOR 27-21-28-820-801, OPERATIONAL TEST OF THE PITCH TRIM SYSTEM 27-41-00-710-801, AND ELECTRICAL RIGGING OF THE PITCH TRIM SYSTEM. ALL CHECKS AND RIGGINGS COMPLETE WITH SATISFACTORY RESULTS. CLOSED UP ACCESS BY REINSTALLED LT EQUIPMENT RACK PANELS. PERFORMED OPS CHECKS OF THE LIGHT AND MED DOOR SWITCH ATTACHED TO THE REINSTALLED PANEL. ALL CHECKS GOOD. POWERED DOWN AIRCRAFT. ALL WORK DONE LAW AMM CH. 27-41-21. OLD HSTECU P/N C47329-012 S/N 642 REPAIRED HSTECU P/N C47329-012 S/N 051
GEAR RED CAS ILLUMINATED - AFTER TAKE OFF DURING CLIMB RED CAS MESSAGE"GEAR". DISAPEARED AFTER 1 SECOND. (INCLUDED CAS MESSAGE "SPOILER FAULT") SPEED 250 AT 6000 FT CLIMBING. CORRECTIVE ACTION, DOWNLOADED FAULT HISTORY AND SPOILER ECU FAILT HISTORY. SENT FILES FOR REVIEW. ADVISED TO CHECK RADIO ALTIMETER ANTENNAS, COAX CABLES AND IF ALL GOOD REPLACE RADIO ALTIMETER BOX. CHECKED RADIO ALT ANTENNAS AND CABLES WITH NO DEFECTS FOUND. CHECKED ANTENNAS BONDING AND FOUND GOOD. REMOVED AND REPLACED DEFECTIVE ALT-4000 ALTIMETER. PERFORMED OPERATIONAL CHECKS WITH NO DEFECTS.
UPON TAKEOFF, THE CABIN & COCKPIT FILLED WITH SMOKE. AFTER COMPLETING SEVERAL VISUAL INSP & CLEANING OF RESIDUAL OIL, RAN APU BLEED AT HIGH FLOW ON MAX HEAT FOR 15 MINS TO START DUCT BURN OUT PROCEDURE. STARTED ACFT ENGS, RAN LT ENG AT HIGH POWER WITH ECS SELECTED TO LT AT HIGH FLOW WITH MAX HEAT FOR 15 MINS. RAN RT ENG AT HIGH POWER WITH ECS SELECTED TO RT AT HIGH FLOW WITH MAX HEAT FOR 15 MINS. RAN BOTH ENGS AT HIGH POWER WITH ECS SELECTED TO BOTH AT HIGH FLOW WITH MAX HEAT FOR 15 MINS. DURING INITIAL ENG RUN A SLIGHT OIL ODOR WAS NOTICED WHICH DIMINISHED BY COMPLETION OF THE RUNS. LEAK CHECK OF DISCONNECTED DUCTS IN RT PYLON ACCOMPLISHED, NO LEAKS NOTED. PERFORMED VISUAL & BORESCOPE INSP OF LINES & ATTACHING HARDWARE UNDERNEATH OUTER DUCT. FOUND NO HARDWARE MISSING, NO BROKEN LINES & NO LEAKS NOTED. COMPLIED WITH IAW MFG MODEL 306A 71-00-00, 79-20-00, 75-30-00, 75-10-00 & AMM 52-40-08.
DURING ACFT MOVEMENT WITH BRAKES INITIALLY APPLIED A GROANING SOUND CAN BE HEARD UNDER COCKPIT FLOOR. WITH PARK BRAKE SET A THUMPING SOUND CAN BE HEARD BELOW PEDESTAL. EXCESSIVE BRAKE PRESS SEEMS TO BE REQUIRED TO RECEIVE NORMAL BRAKING ACTION AT TAXI SPEED. PERFORMED NORMAL BRAKE SYS BLEED IAW AMM 32-40-20. PERFORMED HYD SYS SERVICING IAW AMM 12-15-00.
RIGHT MAIN GEAR WOULD NOT INDICATE UP. COMPLIED WITH QRH PROCEDURES. R & R RT MLG NR 2 UPLOCK SWITCH IN THE AFT POSITION IAW AMM 32-10-11. PERFORMED EXTENSION & RETRACTION FUNCTIONAL TESTS IAW AMM 32-30-00. OPS CHECKED GOOD.
AT 37000 HEARD A POP SOUND & THE LT MFD WENT OUT. A BURNING WIRE SMELL STARTED THEN WENT AWAY AFTER SHUTTING OFF THE RT AVIONICS. PERFORMED INSPECTION OF WIRING BEHIND INSTRUMENT PANEL, NO HIDDEN DAMAGE OR DEFECTS NOTED. R & R THE LT MFD ON CO-PILOT'S SIDE IAW MM 34-21-15, SYS OPERATIONS CHECKED GOOD, NO DEFECTS NOTED.
NOSE WHEEL STEERING INOPERATIVE. TOOK SEVERAL TRIES TO ENGAGE. ONCE ENGAGED IT WAS PULLING RIGHT. IN THE RIGHT TURN TO RETURN TO THE FBO, IT FAILED COMPLETELY, FULL RIGHT.
NOSE WHEEL STEERING INOPERATIVE. TOOK SEVERAL TRIES TO ENGAGE. ONCE ENGAGED, IT WAS PULLING RIGHT. IN THE RT TURN, IT FAIL COMPLETELY FULL RIGHT. COMPLIED WITH NOSE STEERING TROUBLESHOOTING. DURING OPS CHECK, FOUND STEERING TO LT TRAVELS TO FULL DEFLECTION WITH NO DEFECTS, WHEN STEERING TO RT, FOUND STEERING FAIL CAWS MESSAGE COME ON AT 20 DEGREES AND WAS ABLE TO RESET TO NEUTRAL BY TURNING OFF SWITCH. AT 40 DEGREES TRAVELS, WILL NOT RESET TO NEUTRAL UNLESS WHEELS ARE MANUALLY CENTERED. STEERING ECU SHOW VEL LED ON COMPUTER FACE. PERFORMED NOSE WHEEL STEERING FEEDBACK POTENTIOMETER ADJUSTMENT & TEST, STEPS 1A THRU 1B-38 IAW MM 32-50-10. OPS CHECKED GOOD. NO FURTHER DEFECT NOTED.
AFTER TAKEOFF AND ON INITIAL GEAR RETRACTION, RT HYD PUMP PRESS LOW, AUX HYD PUMP ON, AND RT HYD LOW LEVEL CAUTION MESSAGES ILLUMINATED. FLUID QTY LEVEL WAS AT 24 ON RT HYD SYS. RAN QRH PROCEDURES AND LANDED SJC. ON POSTFLIGHT, HYD FLUID NOTED ON BOTTOM ON PLANE FROM DRAIN MAST AFT TO TAIL. FOUND RT FLAP SELECTOR VALVE LEAKING. REMOVED OLD VALVE INSTALLED. REPAIRED VALVE IAW MM 27-52-10. LEAK AND OPS CHECKS GOOD.
ON TAKE OFF, RECEIVED A BLEED PRESS/TEMP HI RED EICAS MESSAGE AT FULL POWER MESSAGE. WENT AWAY WHEN POWER LEVERS WERE PULLED BACK TO IDLE. PERFORMED FUNCTIONAL CHECKS IAW MM 21-00-00 PG 149-151 AND MM 21-11-08 PG-501, ALL CHECKS GOOD-RAN BOTH ENGINES TO POWER OF THE DAY AND COULD NOT REPEAT THIS ITEM. OPS CHECK GOOD AT THIS TIME.