N627QS
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
LT MLG TRAILING LINK HAS SIGNS OF PITTING ON THE INNER WALL. / FOUND WHILE PERFORMING SL680A-32-11. CORRECTIVE ACTION: PERFORMED EDDY CURRENT INSPECTION. NO CRACKS FOUND. OPS CHECK GOOD. IAW CE680A NDTM REV 8 APR 1, 2025
RH MLG TRAILING LINK HAS SIGNS OF PITTING ON THE INNER WALL. / FOUND WHILE PERFORMING SL680A-32-11. CORRECTIVE ACTION: PERFORMED EDDY CURRENT INSPECTION. NO CRACKS FOUND. OPS CHECK GOOD. IAW CE680A NDTM REV 8 APR 1, 2025
DISBONDS ON THE UPPER WINGS BETWEEN THE OUTBOARD END OF STRINGERS AND THE COMMON SKIN DOUBLERS. THE SKIN AND COMMON DOUBLERS MAY ALSO EXHIBIT A GRADUAL DEVIATION FROM CONTOUR IN THESE REGIONS. THE EXTEND OF THE DEFECT IS LOCATED USING ULTRASONIC INSPECTION AND CORRECTED BY ADDING FASTENERS AND ADHESIVE TO THE DISBONDED AREAS. REFERENCE FIELD REPAIR SR-680A-ATA57-47522 DATED 05/MAR/2025.
DENT DISCOVERED ON TOP OF LEFT WING.2). FLAP: RIGHT FLAP HAS A NOTICEABLE DENT ON THE TOP DISCOVERED DURING PREFLIGHT INSPECTION. PERFORMED PERMANENT REPAIR IAW RFTS-112809 AND SPM 20-50-00.
LAV FLOOR EMERGENCY LIGHT INOP. PERFORMED THE "EMERGENCY LIGHTS FAIL PREFLIGHT TEST" PROCEDURE FROM THE QRH. LIGHT REMAINED INOP. FOUND LAV FLOOR EMERGENCY LIGHT CONNECTOR WIRING PIN PULLED FROM CONNECTOR. REINSTALLED PIN OPS CHECK GOOD
LH MLG AXLE PLATING DAMAGE (CHIPPED)
STINGER UPPER NUTPLATE DRAG ANGLES ARE CORRODED AT NUTPLATES.
MAIN EXIT SIGN/LIGHT: MAIN CABIN EXIT LIGHTS ALL REMAIN ON AFTER SHUTDOWN. // SIGNOFF // RESET COCKPIT INERTIA SWITCH IAW CE-680AMM 33-50-11 OPS CHECKS GOOD.
LAV EMERG LIGHT: ON INITIAL EMER LIGHT TEST, FOUND LAV EMER FLOOR LIGHT IMOP. // SIGNOFF// POWERED ON A/C AND CONFIRMED SQWAK REMOVED TOILET FRONT PIECE TO ACCESS FLOOR STRIP CONNECTOR, FOUND CONNECTOR PF2010 PIN PUSHED BACK, REINSERTED PIN AND REINSTALLED TOILET PANEL TURNED ON EMERGENCY LIGHTS AND FLOOR STRIP LIGHT ALONG WITH ALL THE OTHER LIGHTS CAME ON, LEFT A/C POWERED ON FOR 2 HOURS TO LET EMERGENGY BATTERIES CHARGE WORK ACCOMPLISHED JAW C36B0A MM33-50-00 OPS CHECK GOOD.
THE FUSELAGE LOWER SKIN (PN: 7411392-12) WAS CHAFED IN TWO AREAS FROM CONTACT WITH THE ANTI-ICE CROSSFLOW VALVE. THE VALVE IS REPOSITIONED PER TEXTRON AVIATION SB680A-30-10. CHAFE DAMAGE REPAIRED PER TEXTRON AVIATION SR-680A-53-22175, FAA FORM 8100-9 SUBMITTAL LETTER NO. 19-1711 DATED 7/19/2019.
EMERGENCY EXIT SIGN/LIGHT: EMERGENCY LIGHTS WILL NOT TURN OFF WITH SWITCH IN OFF POSITION. LIGHTS ARE OVER THE MAIN CABIN DOOR (WHITE), 2 (RED) SIDE WALL LIGHTS NEXT TO MAIN CABIN DOOR AND UNDER SEAT FACING MAIN CABIN DOOR (WHITE).RESET "G" SWITCH IN COCKPIT PEDESTAL. EMERGENCY EXT LIGHTS EXTINGUISHED. OPS CHECKED GOOD. REF CE-680A M/M 33-50-11.
FOUND DURING INSPECTION: HORIZONTAL STAB AFT PIVOT FITTING CRACKED. P/N 6631102-31.
DURING A SCHEDULED INSPECTION, FOUND THE HORIZONTAL STABILIZER ATTACH FITTING CLIP CRACKED IN TWO PLACES. THE CRACKS WERE IN THE CUT OUT RADIUS ABOUT .12 INCH LONG. CLIP WAS SENT TO FOR EVALUATION. A REPORT WAS FILED UNDER SCR 708902.
SMOKE WAS OBSERVED IN THE COCKPIT & CABIN. ODOR WAS ALSO OBSERVED.
WHILE TROUBLESHOOTING, AN AUTO PILOT PORPOISE DISCREPANCY, THE TECH PULLED ON A PRIMARY RUDDER CABLE IN THE TAIL CONE AND IT SNAPPED. THE CABLE HAS BEEN BROKEN EXCEPT FOR A FEW STRANDS. IT APPEARS THE CABLE WAS NOT RIDING IN A PULLEY AND WAS CHAFING ON THE UPPER CABLE GUARD. INCORRECT ROUTING MAY HAVE BEEN THE ROOT CAUSE FOR THE POTENTIAL FAILURE. 2 SETS OF EYES AR CRITICAL WHEN WORKING ON PRIMARY FLIGHT CONTROL SYS AND CRITICAL ACFT COMPONENTS.
APPROX 1 HR INTO A FLIGHT, AT 41,000 AND IN NORMAL CRUISE MODE. CO-PILOT AND PILOT COULD DETECT AN ODOR OF FUEL. WENT TO BACK OF PLANE WHERE FOUR OTHER CREW MEMBERS COULD DETECT IT AS WELL. DURING DESCENT IT WASN'T AS NOTICABLE AT LOW POWER SETTINGS. INCREASED POWER AT INTERMEDIATE LEVEL OFFS, THE ODOR WOULD RETURN. TRIED TO ISOLATE THE ODOR BETWEEN THE LT & RT PRESSURE SOURCE BUT COULDN'T NOTICE ANY DIFFERENCE. PERFORMED ENGINE RUNS WITH BLEEDS ON TO SIMULATE WRITE-UP. NO FUMES WERE DETECTED AT THIS TIME UTILIZING A MULTIGAS DETECTOR SET ON THE JET A FUEL SETTING & RUNNING BOTH ENGINES AT ALL POWER SETTINGS.
DISTINCT EXHAUST ODOR IN COCKPIT AT TAKE OFF WITH APU ON AND APU BLEED AIR ON. WITH BLEED AIR OFF THE ODOR IS REDUCED. IN FLIGHT THERE IS AN EXHAUST ODOR (NOT AS DISTINCT). IT IS REDUCED WHEN EITHER PRESS SOURCE IS SELECTED. FOUND APU OIL OVERSERVICED. REMOVED OIL TO CORRECT LEVEL. IAW MM 12-11-03. INSPECTED WATER SEPARATOR/ COALESCER SOCK FOUND RESIDUAL OIL & DIRTY ODOR. REPLACED SOCK "NEW". MX IAW MM 21-51-00. FOUND APU FLOW DIVIDER TEE B-NUT - LEAKING FUEL AT APU PRIMARY FUEL MANIFOLD. TIGHTENED B-NUT. MX IAW MM 49-30-06, OPS CHECK GOOD.
AT FL 430, WITH PFD 2 SELECTED (RT SEAT FLYING) LT PFD COMMAND BAR TURNED BLUE ALONG WITH ALL TREND BARS AND COURSE INDICATORS. THE RED AIRSPEED TAPE DISSAPEARED AND THE ATTITUDE GYRO TURNED TO GRAY, VICA, BLUE AND BROWN. REPOSITIONED THE NR 1 PFD TO THE MFD POSITION, AND THE MFD TO THE NR 1 PFD POSITION IAW THE MM 34-25-01. OPS CHECK OF BOTH UNITS GOOD. MONITORED SYS FOR SEVERAL HOURS WITH NO DEFECTS NOTED.
AFTER TAKE OFF (L) FUEL GUAGE ANNUNCIATOR ILLUMINATED. FUEL LOAD INITIALLY SHOWED 1000 LBS HIGH, THEN STABILIZED SHOWING 1000 LBS LOW AND REMAINED THERE.
MOVING THE FUEL TRANSFER SWITCH FROM LT TO OFF CAUSES THE L/R LOW PRESS ANNUN. TO ILLUMINATE MOMENTARY & TURN THE L/R FUEL BOOST PUMP ANNUN. ON. TROUBLESHOT TO RT MOTIVE FLOW VALVE. R & R VALVE IAW MM CH 28-21-06. OPS & LEAK CHECK GOOD.
LEFT GREEN DOWN AND LOCKED ANNUNCIATOR ILLUMINATED INTERMITTENTLY IN FLIGHT. HYDRAULIC PRESS LIGHT DID NOT ILLUMINATE. ALL OTHER INDICATIONS NORMAL. INSTALLED REPAIRED ACTUATOR IAW THE MM 32-30-04. OPS CKED GOOD
AT BEGINNING OF TAKEOFF ROLL THE RT FUEL QUANTITY INDICATOR DROPPED TO ZERO AND THE RT FUEL GAUGE ANNUNCIATOR AND MASTER CAUTION ILLUMINATED. STARTED APU AND WAITED 15 MIN. CHECKED SIGNAL CONDITIONER LED'S NO FAULTS DISPLAYED. STARTED ENGINES & TAXIED ACFT. MONITORED RT FUEL GAUGE, NO FAULTS, ALL INDICATIONS NORMAL. SUMPED FUEL FROM TANKS, FUEL REMOVED CONTAINED A SMALL AMOUNT OF WATER. RAN ENGINES & TAXIED AGAIN. DURING TAXIING EXECUTED SEVERAL AGGRESSIVE STEERING MANEUVERS. NO FAULTS FOUND OR DISPLAYED. PERFORMED AN ADDITIONAL COMPLETE SHUTDOWN FOLLOWED BY ANOTHER FULL START OF ENGINES. NO FAULTS FOUND OR DISPLAYED ON SIGNAL CONDITIONER. REINSTALLED ACCESS PANELS.
DURING ROUTINE INSP, FOUND CABLE STRANDS BROKEN AND FRAMED. THE DAMAGED AREA OF THE CABLE IS WHERE IT GOES OVER A SERIES OF "S" PULLEYS MOUNTED IN THE HORIZ STAB. SHOULD MAKE THIS A TIME CHANGE ITEM. (K)
BOTH L/R FUEL GAUGE ANNUNCIATORS ILLUMINATED ON TAKEOFF. TAKEOFF WAS ABORTED. FUEL QTY GAUGES BOTH READ ZERO. GAINED ACCESS TO LT/RT WING ROOT ELECTRICAL CONNECTORS FOR MOISTURE NONE FOUND. INSPECTED FUEL SIGNAL CONDITIONER FOR FAULT BITES NONE FOUND.
ON TAKEOFF ROLL, MASTER CAUTION CAME ON, REJECTED TAKEOFF, LT FUEL GAUGE ANNUNCIATOR LIGHT ON. CONNECTED TEST SET, FOUND PROBE NR 6 READING LOW. REMOVED NR6 PROBE, CLEANED AND REINSTALLED, PROBE NOW READING IN SAME RANGE AS OTHER PROBES, C/W WET CAL IAW MM CH 28-41-00. OPS CHECKED GOOD. LEAK CHECKED GOOD.
ON TAKEOFF, GOT A STAB MISCOMPARE LIGHT AND THE HYDRAULIC PRESS LIGHT. REPLACED ACTUATOR DUE TO EXCESS LEAKAGE IN ACTUATOR IAW 560XL M/M 23-40-00. OPS AND LEAK CHECK GOOD.
LT BRAKE IS STICKING CAUSING CONTROL ISSUES WHILE TAXIING. INSTALLED AN OVERHAULED BRAKE IN LT POSITION IAW MM CH 32-42. INSTALLED AN OVERHAULED METERING VALVE IN LT POSITION IAW THE MM CH 32-42.
DURING ROUTINE INSPECTION FOUND MAIN ENTRY DOOR PUSHROD (OPENING/CLOSING) RUBBING AGAINST THE CUTOUT IN THE DOOR STRUCTURE. ADJUSTED PUSHROD TO PREVENT CHAFING, PERFORMED BLEND OUT REPAIR TO CABIN DOOR FORMER IAW MFG REPAIR DEFINITION REPORT NR S-560XL-5227/01RD.