N673QS
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: MAIN ENTRANCE DOOR IS VERY HARD/HEAVY TO CLOSE THE LAST 2 FEET OF MOVEMENT. WHEN OPENING DOOR, IT POPS OPEN ABOUT 2 FEET AND PULLED CREWMEMBER INTO DOOR. CORRECTIVE ACTION: OPENED AND DOSED DOOR MULTIPLE TIMES, FOUND DOOR COUNTER BALANCE ASSIST NOT ALLOWING DOOR TO HAVE FULL ASSIST, INSPECTED DOOR CABLES AND FOUND FRAYING ON AFT CABLE, ALSO NOTED TENSION SEEMED LOW WHEN FEELING BY HAND, CONTACTED AMCC AND ORDERED TWO NEW DOOR COUNTER BALANCE CABLES AND ALSO ORDERED CABLE TENSIOMETER FROM WEST STAR LOGISTICS Ãâ¬Â¢. 5/5/25 D.P, J.G RECEIVED CUSTOMER SUPPLIED PARTS, REMOVED AND REPLACED FORWARD AND AFT MAIN CABIN DOOR COUNTERBALANCE CABLES WITH NEW I.A.W CE-560XL M/M CHAP 52-10-03, TENSIONED CABLES AS REQUIRED, OPS CHECK SATISFACTORY. CABLE TENSIOMETER TL-105556
MAIN DOOR: MAIN ENTRANCE DOOR IS VERY HARD/HEAVY TO CLOSE THE LAST 2 FEET OF MOVEMENT. WHEN OPENING DOOR, IT POPS OPEN ABOUT 2 FEET AND PULLED CREWMEMBER INTO DOOR.
DURING DOOR CLOSURE, BOTH LIGHTS GO OUT BRIEFLY. WITHIN A FEW SECONDS THE "CABIN DOOR" LIGHT COMES BACK ON. IT BAS BEEN INTERMITTENT ALL WEEK. IT WOULD GO OUT AFTER OPENING AND CLOSING. THIS TIME WE TRIED NUMEROUS TIMES, INCLUDING MANUALLY TRYING TO PUSH THE VENT DOOR CLOSED. REMOVED AND REPLACED THE MAIN DOOR VENT SOLENOID IAW AMM 52-70-00.OPERATIONAL TESTS GOOD.
MAIN DOOR: AFTER LANDING, WE HAD TO CYCLE THE DOOR LOCK TO OPEN THREE TIMES TO GET THE DOOR TO OPEN. PRECATCH HANDLE WAS PULLED AND DID NOT HELP THE SITUATION. THE ACOUSTIC SEAL WAS NOT THE ISSUE EITHER. DOOR HANDLE IS EXTREMELY STIFF WHEN CLOSING AND OPENING THE DOOR. OPENED MCD AND OPERATED DOOR LATCHES WHILE DOOR WAS OPEN AND FOUND ALL OPERATIONAL DOOR LATCHES WHILE DOOR WAS OPEN AND FOUND ALL OPERATION SMOOTH CLEANED AND LUBED MCD PINS CLOSED MCD AND OPERATED MCD AND OPERATED DOOR FROM INSIDE FOUND DOOR HANDLE DIFFICULT TO OPERATE. ADJUSTED MCD PIN SOCKETS IAW AMM 52-10-00 AND OPERATED MCD MULPLE TIMES PWR AIRCRAFT AND RAN APU OPERATED MCD MULTIPLE MORE TIMES WITH NO FUTHER DISCEPANCY NOTED. ALL OPS ALL OPS CHECKS ALL OPS CHECKS GOOD AFTER ADJUSTMENT
CREW CAN NOT CLOSE CABIN DOOR FROM INSIDE. EVIDENCE OF SCARRING WHERE TOP FWD ROUND PIN ENGAGES LATCH PIN PLATE IN FRAME. INSPECTED DOOR LOCK PINS & BEARING PLATES. ADJUSTED AS REQUIRED. OPS CHKD DOOR, DOOR CLOSES BUT REQUIRES EXCESSIVE FORCE. INSP HANDLE ASSY, BELLCRANK ASSYS. REMOVED STEPS, INSP INTERNAL PARTS, NO DEFECTS. INSTALLED STEPS & ATTACHED ELEC CONNECTOR. WORK DONE IAW AMM 52-10-00. INSPECTED DOOR SUPPORT STRUT, HANDRAIL & ACTUATING LEVER, FOUND SUPPORT STRUTS LOOSE, ADJUSTED & SECURED TO DOOR. OPS CHECKED DOOR, ADJUSTED TOP LATCH PLATES & PRECATCH ADJUST PLATES, CLOSING IMPROVED, STILL REQUIRES EXCESSIVE FORCE TO CLOSE FROM THE INSIDE. DONE IAW AMM 52-10-00.
FORWARD CABIN EMERGENCY LIGHT SYSTEM WILL NOT EXTINGUISH UNLESS TURNED OFF WITH THE SWITCH. SUSPECT INERTIA SWITCH. GAINED ACCESS TO FWD EMER BAN AND FOUND THAT THE INERTIA SWITCH TRIPPED. RE-SET SWITCH AND CW OP'S TEST OF EMER LIGHTS, OP'S TEST GOOD IAW MM 33-50-01. ORIG SUB DATE: 1/24/2023
WITH THE EMERGENCY LIGHT SWITCH ON AND BATTERY SWITCH OFF, THE EXIT SIGN OVER SEAT 7 AND EXIT SIGN OVER LAV IS VERY DIM. TURNING BATTERY SWITCH ON BOTH LIGHTS ILLUMINATE NORMAL. REMOVED FORWARD EMERGENCY LIGHTING BATTERY PACK AND INSTALLED CUSTOMER SUPPLIED TESTED EMER BATTERY. REMOVED THE AFT EMERGENCY LIGHTING BATTERY PACK AND INSTALLED CUSTOMER SUPPLIED OVERHAULED EMERGENCY LIGHTING BATTERY PACK. CHARGED THE BATTERIES AS REQUIRED AND PERFORMED OPS CHECKED. NO DEFECTS. ORIG SUBMISSION DATE: 1/19/2023
NR 2 ENGINE FAILED ON TAKEOFF AT GEAR RETRACTION. HEARD LOUD BANGS AND THE ITT SPIKED AT THE TOP OF RED. ENGINE WAS NOT PRODUCING POWER AT THIS POINT. FOLLOWED SOPS, RAN CHECKLISTS, SHUT ENGINE DOWN & BACK FOR LANDING. FELT VIBRATIONS COMING FROM THE ENGINE AFTER SHUT DOWN IN FLIGHT. NO INDICATIONS OF FIRE FOUND. NO VISIBLE DAMAGE FROM OUTSIDE, BUT THE ENGINE NOT WINDMILLING IN THE WIND. REMOVED THE ENGINE INSTALLED AN INSPECTED A SERVICEABLE ENGINE. PERFORMED FOLLOW ON CHECKS AS REQUIRED WITH SATISFACTORY RESULTS, NO LEAKS NOTED. MAINTENANCE ACCOMPLISHED IAW AMM 71-00-03.
AFTER RE-SERVICING OF THE NLG STRUT PRESSURE HELD BUT THE FLUID BYPASSED SEAL. DURING RE-SEAL OF NLG, FOUND CORROSION IN UPPER BARREL. DISASSEMBLED, CLEANED AND VISUALLY INSPECTED. FOUND MISC BEARINGS, SEALS AND HARDWARE WORN. FOUND RING PACK AND RETAINER CORRODED. FOUND METERING PIN DAMAGED.
AT 220 KTS, 1500 FT, MOVED THE GEAR HANDLE TO THE DOWN POSITION. HANDLE MOVED NORMALLY AND LOCKED INTO PLACE BUT ONLY THE RED GEAR UNSAFE LIGHT CAME ON AND NO SOUNDS OF THE GEAR DOORS OPENING. AFTER WIGGLING THE HANDLE BACK AND FORTH FOR 4-5 SECONDS IN THE DOWN POSITION THE GEAR EXTENDED NORMALLY. R & R LANDING GEAR HANDLE IAW MM 32-30-01. OPS CHECKS GOOD.
DURING A VISUAL INSPECTION OF THE FORWARD CABIN DOOR HINGE FITTING, FOUND CRACK. CRACK .35 INCHES LONG AND WAS IN THE RADIUS AREA BETWEEN THE FLANGE AREA THAT ATTACHES TO THE FUSELAGE. THE CRACK WAS VERIFIED USING DYE PENETRANT METHOD. HINGE FITTING WAS REPLACED WITH NEW.
DURING A VISUAL INSPECTION, FOUND CORROSION ON CABIN DOOR HINGE FITTING, LIMITED TO THE INWARD EDGE OF THE HINGE FITTING, ON CLOSER INSPECTION, FOUND A CRACK THAT WAS .35 INCH LONG ON THE HINGE FITTING RADIUS AREA BETWEEN THE FLANGE ATTACH BRACKETS. THE CRACK WAS VERIFIED BY USING DYE PENETRANT METHOD. HINGE FITTING WAS REPLACED WITH NEW.
DESCENDING THROUGH 11,500 FT WITH AN AIRSPEED OF 250 KTS. HAD GEAR WARNING AURAL INDICATION. IN CRUISE CONFIGURATION 11,000 AGL. HAD AN ADDITIONAL 4 AURAL WARNING LASTING FROM 3 SECONDS TO 25 SECONDS DURING THE REMAINDER OF FLIGHT. ALSO HAD AN EGPWS WARNING DURING ONE OF THE GEAR WARNING EVENTS. CHECKED WIRING CONNECTIONS, BOND CHECKED ANTENNAS, RANG COAXS, ALL GOOD. PREFORMED LANGING GEAR WARNING CHECK & THROTTLE SWITCH TEST, NO FAULTS NOTED. INTERIGATED EGPWS & FOUND SEVERAL "TO LOW TERRAIN" IN FLIGHT WARNINGS, TECH CHANGED RADIO ALT TRANSCEIVER, PLACED SPEX UNIT IN ACFT SET RADIO TO ZERO FT, OPS CHECKED GOOD IAW MM CH 34-12-10.
GEAR WARNING HORN SOUNDED ON 3 SEPARATE OCCASIONS. FIRST, FOR 30 SECONDS AT IAS OF 210 KTS & FL220, FLAPS 0. INCREASE OR DECREASE OF THROTTLE SETTING WOULD NOT EXTINGUISH HORN. SECOND, HORN SOUNDED FOR ABOUT 10 SECONDS, AT 210 KIAS APPROACHING 8000 FT. THIRD, HORN SOUNDED FOR JUST A FEW SECONDS AS GEAR SELECTED & FLAPS SELECTED TO 35 ON TURN TO FINAL. INSPECTED AND SYSTEM OPERATES NORMALLY AT THIS TIME ON THE GROUND. WORK DONE IAW AMM 7-10-01, 27-51-00, 29-11-07 AND 34-11-01.
REMOVED GEAR CONTROL HANDLE ASSY AND REPLACED WITH REPAIRED UNIT. OPS CHECKED CYCLED LANDING GEAR OPS CHECK GOOD. WORK DONE IAW MM 32-30-01.
LANDING GEAR SELECTOR HANDLE MOVED TO DOWN. RED UNLOCK LIGHT ILLUMINATED BUT GEAR DID NOT COME DOWN. THREE SECONDS LATER GEAR CAME DOWN. REMOVED DEFECTIVE LANDING CONTROL UNIT AND INSTALLED A REPAIRED CUSTOMER SUPPLIED UNIT. WORK DONE IAW AMM 32-30-01. COMPLIED WITH 4 GEAR SWINGS IAW AMM 32-30-05. OPS CHECKED GOOD.
REMOVED RT MAIN GEAR WHEEL BRAKES ASSY. INSTALLED O/H CUSTOMER SUPPLIED MAIN GEAR WHEEL BRAKE ASSY. PERFORMED EMERGENCY BRAKE SYS OPS CHECK AND BLED THE ANTISKID BRAKE SYS WITH NO DEFECTS NOTED. ALL WORK DONE IAW MM CHAP 32-42-01.
ON LANDING, WHEN BRAKES ARE APPLIED THE AIRPLANE YAWS TOWARDS THE RT. REMOVED RT MAIN GEAR WHEEL BRAKES ASSY. INSTALLED O/H CUSTOMER SUPPLIED MAIN GEAR WHEEL BRAKE ASSY. PERFORMED EMERGENCY BRAKE SYS OPS CHECK AND BLED ANTI-SKID BRAKE SYS WITH NO DEFECTS NOTED. ALL WORK DONE IAW MM CHAPTER 32-42-01.
WHEN GEAR HANDLE WAS LOWERED RED GEAR UNLOCK ILLUMINATED; NO GREEN GEAR LIGHTS, NO HYD PRESS LIGHT. AFTER 20 SEC GEAR CAME DOWN NORMALLY. REMOVED AND REPLACED LANDING GEAR CONTROL PCB PER MAINT. CONTROL REQUEST IAW MM 24-51-02. ACCOMPLISHED GEAR SWINGS, OPERATIONAL CHECK GOOD.
(RT LO OIL PRESS) LIGHT CAME ON DURING T/O, WHICH WAS ABORTED. 09-28-07 REMOVED AND REPLACED NR 2 ENGINE WITH SERVICEABLE UNIT USING NEW SEALS. ALL ACCESSORIES AND WIRE HARNESS SWAPPED TO INSTALLED ENGINE WORK PERFORMED PER CESSNA 560XL M/M 71-00-03 AND PRATT& WHITNEY 545B M/M 71-00-00. OPS AND LEAK CHECKS GOOD.
AIRCRAFT WILL NOT CROSSFEED IN FLIGHT. HAD NORMAL INDICATIONS OF CROSSFEED BUT NO FUEL TRANSFER FROM LT TO RT. TRANSFER FROM T TO LT HAD BOTH LOW FUEL PRESSURE LIGHTS AND LT BOOST PUMP ILLUMINATED. NO CROSSFEED LIGHT INDICATION. ON THE GROUND STILL NO FLOW INDICATION WHEN CROSSFEEDING LT TO RT. ATTEMPTING TO CROSSFEED RT TO LT ONLY CROSSFEED LIGHT INDICATION. RT BOOST PUMP ON, NO INDICATION OR NOISE. 09-27-07 T/S TO INTEMITTENT RT FUEL BOOST "CB" & RT FUEL PC BOARD REMOVED & REPLACED RT FUEL "CB" & RT FUEL PC BOARD. RAN FOR OPS CHECKS. SYSTEM OP'S CHECKS SATISFACTORY AT THIS TIME. ALL WORK DONE IAW CE560XL MM 24-00-00 & 28-20-00.
DURING TAXI BRAKES RUMBLE WHEN PRESSURE IS APPLIED. CONDITION REPEATS ON PILOT AND COPILOT SIDES. RUMBLING OCCURED DURING SLOW TAXI (LESS THAN 10 KTS). RUMBLING ACTS LIKE LOW SPEED ACTIVATION ON ANTI-SKID (PULSING BRAKES). REPLACED BRAKE METERING VALVE WITH NEW FROM MFG IAW CHAPT 32-44-20 OF CE560XLS MM. VALVE BLED AND RIGGED AS NEEDED IAW CHAPT 32-44-00 OF CE560XLS MM. SYSTEM SERVICED AND SAFETIED AS NEEDED. OPERATIONAL AND FUNCTION TESTED GOOD. TAXI CHECK GOOD.
EVERY TIME THE BRAKES ARE INITIALLY APPLIED, WILL GET A RUMBLE/VIBRATION FROM BOTH BRAKES FOR 2-3 SECONDS FOLLOWED BY NORMAL BRAKING. IF BRAKE PRESSURE IS RELEASED THEN REAPPLIED, WILL GET THE RUMBLE/VIBRATION. REMOVED LT BRAKE ASSY, 2-1601-, S/N 1303 AND INSTALLED BRAKE P/N SAME, S/N 0105. CLEANED, INSPECTED AND REPACKED LT WHEEL BEARINGS. NO DEFECTS NOTED. INSPECTED LT WHEEL BRAKE LUGS. NO DEFECTS NOTED. REINSTALLED ORIGINAL WHEEL. TORQUED AND SAFETIED NUT. TAXIED A/C AND APPLIED VARIOUS BRAKE APPLICATIONS AND DIFFERENT SPEEDS. NO RUMBLE OR VIBRATIONS WERE HEARD OR FELT. OPS CHECK GOOD. ALL WORK PERFORMED IAW MM CHPT 32-41-02, 32-44-00, 32-42-01.