N385QS
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
SHORTLY AFTER TAKEOFF POWER APPLIED, HP VALVE FAIL LT AMBER CAS LIGHT ILLUMINATED. COMPLETED APPROPRIATE QRH. INSPECTED GD001 GROUND. NO DISCREPANCIES. RANG WIRING FROM VALVE TO PYLON,. NO DISCREPANCIES. R & R HP VALVE. OPS CHKD GOOD, BUT LEAK CHECKS NOT GOOD. INSTALLED GASKET SEALS . STILL LEAKS. R & R COUPLINGS HOLDING THE HP VALVE WITH TWO NEW GRAFOIL SEALS. LEAK CHKD GOOD. WORKED IAW MM 20-10-40.
REPAIRED CORRODED AREAS OF THE LOWER AFT TAILCONE SKINS, LOCATED UNDER AND ADJACENT TO THE AFT CHIN FAIRING JOINT, BY BLENDING AREAS, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING REPAIR DOUBLERS PER ENGINEERING REPAIR ORDER.
REPAIRED THE CORRODED AREA ON THE RT SKIN/PANEL OF THE NOSE LANDING GEAR TUNNEL BY BLENDING CORRODED AREA, PERFORMING NDT, REPORTING FOR REPAIR DISPOSITION, FABRICATING AND INSTALLING REPAIR DOUBLER IN ACCORDANCE WITH ENGINEERING REPAIR ORDER.
BLENDED CORRODED AREA ON THE OUTER SKIN OF THE EMERGENCY EXIT DOOR IN THE LOWER AFT CORNER, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED AREA PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.
BLENDED AREA OF CORROSION LOCATED INSIDE RIGHT MAIN GEAR WELL BAY 720DR ON THE LOWER AFT SPAR CAP, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED BLENDED AREA PER TECHNICAL DISPOSITION REPORT.
BLENDED AREA OF CORROSION LOCATED ON THE LT AFT WING SPAR LOWER WEB AT THE EMERGENCY BRAKE CARRY THROUGH FITTING HOLES, LOCATED IN THE LT MAIN LANDING GEAR WHEEL WELL , PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED BLENDED AREA PER REQUEST FOR TECHNICAL DISPOSITION REPORT.
BLENDED AREA OF CORROSION LOCATED INSIDE LH MAIN GEAR WELL BAY ON THE AFT LOWER SPAR CAP, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED BLENDED AREA PER NETJETS REQUEST FOR TECHNICAL DISPOSITION REPORT.
TEMPERATURE CONTROL: DIVERTED DUE TO AMBER EMERGENCY PRESSURIZATION AND ACM O'TEMP CLIMBING THROUGH APROX 37,000 FT THE RIGHT ENGINE ITT BEGAN TO CLIMB RAPIDLY. PULLED BACK RIGHT THROTTLE APROX 2 FULL KNOB WIDTHS TO AVOID OVERTEMP. EVENT BUTTON WAS PUSHED. SHORTLY THEREAFTER, GOT AMBER EMERGENCY PRESSURIZATION FOLLOWED BY AMBER ACM O'TEMP MESSAGES. CABIN GOT EXTREMLY HOT. CORRECTIVE ACTION; REPLACED DEFECTIVE ACM IAW CE-680 AMM 21-51-00. LEAK AND OPS CHECK GOOD.
CORROSION, LH WING, AFT SPAR, WS 28. ACCOMPLISHED TEXTRON AVIATION FIELD REPAIR FR-680-0115-12138 REV-, DATED JULY 11, 2023 AND FAA FORM 8100-9 DATED 7/11/2023; FIELD REPAIR - CORROSION, LH WING, AFT SPAR, WS 28.
LH HORIZONTAL WIPER PANEL LOWER AFT SECTION MOUNTING HOLES ARE OVERSIZED AND ELONGATED. REFERENCE TEXTRON AVIATION ENGINEERING MEMO DQ31281M1 REV A DATED 31/AUG/2021.
HYDRAULIC LINE: HYDRAULIC PRESSURE LOW L-R AMBER CAS BOTH EMERGENCY GEAR BLOWDOWN AND EMERGENCY BRAKING APPLIED. PERFORMED MULTIPLE GEAR SWINGS WITH THE HYDRAULIC MULE. DURING INITIAL SWINGS FOUND THE CYCLE TO TAKE MORE THAN 125 WITH 3100 PSI IN THE SYSTEM.CONTINUED TO CYCLE THE GEAR UNITL THE GEAR WAS WITHIN THE ALOTTED TIME OF 85 +/-1S. GOT SWINGS TO BE APPORX 6.6 SECONDS ON EXTENSION WITH 7.74S ON RETRACTION. DOWNJACKED AIRCRAFT AND RELOCATED AIRCRAFT TO BLAST FENCE. STARTED THE ENGINES AND FOUND NO DEFECTS UPON POWER UP. CYCLED ALL HYDRAULICALLY POWERED ITEMS AND FOUND THE RESERVOIR TO BE UNDER THE MIN. SERVICED THE RESERVOIR TO PROPER LEVEL AND NO FURTHER DEFECTS NOTED.ALL MX CW IN REF TO CE-680 AMM 32-30-00 AND 12-12-02.
MAIN DOOR: COULD NOT OPEN MAIN CABIN DOOR USING RED RELEASE BUTTON OR SECONDARY RELEASE. WITH ASSISTANCE OF GROUND PERSONNEL WE WERE OPEN DOOR. "CORRECTIVE ACTION" PERFORMED CABIN DOOR INSPECTION/CHECK PER CE-680MM 52-10-00. AS FOLLOWS. REMOVED CENTER ACCESS PANELS PERFORMED DETAILED INSPECTION OF CABIN DOOR SOLENOID WIRINGS. NO DEFECTS NOTED. PERFORMED DETAIL INSPECTION OF INTERNAL LINKAGE, NO DEFECTS NOTED WHEN OPERATING THE HANDLES INTERNALLY OR EXTERNALLY. OPS NORMAL. NO BINDING NOTED. COMPLIED WITH CABIN DOOR SOLENOID FUNCTIONAL CHECK SOLENOID CHECKED GOOD. ACCOMPLISHED CABIN DOOR VISUAL INSPECTION CHECK ALL DOORS SEALS. HANDRAIL PLUNGER NOT DEFECTS NOTED. RUN THE AIRCRAFT TO PRESSURIZED THE DOOR SEALS AND SIMULATE THE DISCREPANCY AFTER THE ENGINE SHUT DOWN. OPENED AND CLOSED THE MAIN ENTRY DOOR MULTIPLE TIMES I COULD NOT DUPLICATED DISCREPANCY. THE MAIN ENTRY DOOR OPERATION CHECK GOOD DURING THE TEST. REF CE-680 MM 52-10-00
CORROSION, WING UPPER SKINS, WS37. ACCOMPLISHED TEXTRON AVIATION STANDARD REPAIR SR-680-ATA57-27245 REV - DATED 10/08/2020; STANDARD REPAIR - CORROSION, WING, UPPER SKINS, WS 37.AFFECTED PART (S); SKIN P/NS 6921370-1, 6921372-9, 6922377-39, 6922680-23, 6922680-24, 6922681-71.
OVER SIZED HOLE, UPPER CENTER WING SKIN WS 36.5 AT THE MAIN SPAR. ACCOMPLISHED TEXTRON AVIATION FIELD REPAIR FR-680-0115-8872 REV - DATED 02/08/2021; FIELD REPAIR - HOLE OVERSIZE, CENTER WING, UPPER SKIN, WS 36.5 AT THE MAIN SPAR.
OVERSIZED HOLE CENTER WING UPPER SKIN WS 36.5 AT THE REAR SPAR. ACCOMPLISHED A FIELD REPAIR FR680-0115-8859 REV - DATED 0/4/2021; FIELD REPAIR - HOLE OVERSIZE, CENTER WING, UPPER SKIN, WS 36.5 AT THE REAR SPAR.
REPAIR TO HORIZONTAL TRAILING EDGE PANELS. TEXTRON AVIATION ENGINEERING REPAIR LETTER DQ28656M2 DATED FEB. 7, 2021.
REPAIR TO ANTI-ICE PICCOLO TUBE FLANGE. TEXTRON AVIATION ENGINEERING REPAIR LETTER DQ28735 DATED JANUARY 30, 2021.
LEFT HAND WING TO FUSELAGE MID FAIRING DAMAGED. REPAIRED L/H WING TO FUSELAGE MID FAIRING P/N 6922706-17 I.A.W TEXTRON AVIATION ENGINEERING DQ28747, REF. S-750-ATA51-01RD REV A.
NLG WHEEL WELL OVERHEAD STRUCTURE FRAME IS CRACKED-UPPER MID UPPER. REFERENCE AQRD ENGINEERING REPAIR ORDER NO. ERO-104483 REV IR DATED JAN 25 2021
CABIN ALTITUDE AMBER CAS ILLUMINATED - ON CLIMB OUT AT 20000 FEET WE OBSERVED CABIN CLIMBING HIGHER THAN NORMAL AND AT 34000 FEET THE AMBER CAS (8500) LIGHT ILLUMINATED. EMERG CHECKLIST WAS ACCOMPLISHED WTIH NO CHANGE AND AN EMERGENCY WAS DECLARED AND CABIN RED ALTITUDE CAS WAS ILLUMINATED AND EMERGENCY DESCENT WAS ACCOMPLISHED AND CAS MESSAGES EXTIGUISHED. DURING THE EMERGENCY THE AMBER ANTISKID LIGHT ILLUMINATED AND WENT OUT. PERFORMED BITE TEST OF THE PRESSURIZATION CONTROLLER IAW AMM 21-30-00, WITH NO DEFECTS NOTED. PERFORMED A VISUAL INSPECTION OF THE OUTFLOW VALVES TO CHECK FOR OBSTRUCTIONS, NO DEFECTS NOTED. INSPECTED AFT EQUIPMENT BAY PLUMBING AND FOUND A LINE FROM THE ACM PRECOOLER DISCONNECTED. PERFORMED A VISUAL INSPECTION FOR DAMAGE, NONE NOTED. SECURED THE LINE IAW AMM 20-LD-40. PERFORMED MANUAL PRESSURIZATION AND LEAK CHECK IAW AMM 21-30-00 PARAGRAPH 5. NO DEFECTS NOTED. OPERATED THE MLG BRAKES MULTIPLE TIMES, VISUALLY INSPECTED MLG WIRE HARNESS AND WHEEL WELL WIRING WITH NO DEFECTS NOTED.
BLENDED AND TREATED 28 AREAS OF CORROSION ON THE CABIN ENTRY DOOR INNER DOOR SKIN ACCESS PANELS PER REPAIR MEMO.
REPAIRED 22 CORRODED AREAS OF THE DROPPED AISLE FLOOR (INTERIOR FUSELAGE SKIN) BY BLENDING AREAS, PERFORMING ULTRASONIC AND EDDY CURRENT INSPECTIONS, TREATING, PRIMING, AND INSTALLING REPAIR DOUBLERS AS REQUIRED IAW ENGINEERING REPAIR ORDER ERO-936469 REV IR, APPROVED BY FAA FORM 8110-3 DATED 18 FEB 2019.
ELONGATED & OVERSIZED HOLES AT BS 624 FRAME IN TAILCONE FOR RUDDER BIAS ATTACHMENT.
CENTER SPAR BULKHEAD AND LEFT AND RIGHT WING STATION 37.0 RIB FITTING CORRODED.
AFT LEFT AND RIGHT SIDE SPAR WEB BULKHEAD FITTING CORRODED.
AFT LEFT AND RIGHT SIDE SPAR WEB BULKHEAD FITTING CORRODED.
SMOKE IN THE CABIN ON THE GROUND WITH THE APU RUNNING & BLEED AIR ON. DISCONNECTED BLEED AIR DUCT COUPLING & BORESCOPED APU INLET COMPRESSOR AREA & BLEED AIR PORT FOR OIL LEAK. NO OIL LEAKAGE NOTED AT THIS TIME. CONNECTED BLEED AIR COUPLING, LEAK CHECK NORMAL. WORK PERFORMED IAW CHAPTER 49-10-00 OF THE MM. POWERED UP ACFT TO RUN APU & SMELLED BURNT WIRING SMELL FROM COCKPIT. ISOLATED BURNED ODOR TO AFT CLOSET. GAINED ACCESS TO CABIN RECIRCULATION FAN. REMOVED CABIN RECIRCULATION FAN & OPS CHECKED. FOUND RECIRCULATION FAN BLOWING BURNED ODOR. INSTALLED REPAIRED EXCHANGE CABIN RECIRCULATION FAN IAW MM 21-22-03. OPS CHECKED NORMAL.
NO TAKEOFF MSG, DUE TO ROLL SYS. UPON INITIAL OPS CHECKS NOTED NO CAS MSGS. REMOVED THE ACCESS PANEL & INSPECTED THE PROXIMITY SWITCH & TARGET. NOTED THE TARGET IS NOT FULLY CENTERED ON THE PROXIMITY SWITCH. REMOVED THE BELLY PANEL & FURTHER INSPECTED. CONFIRMED THE ACTUATOR IS NOT FULLY INTO POSITION. INSTALLED THE TEST HARNESS & OPERATED THE SYS. NOTED RETRACTION IS SMOOTH & THE EXTENSION SOUNDS ROUGH. CYCLED SEVERAL TIMES & THE SYS STARTED OPERATING CORRECTLY. THE ROLL RATIO ACTUATOR IS FAULTY. 05 20 2015 19:11:06 REMOVED THE VARIABLE RUDDER BIAS RATIO ACTUATOR PN 9914749-3 & SN 0437. INSTALLED AN OVERHAULED VARIABLE RUDDER BIAS RATIO ACTUATOR PN 9914749-3EX & SN D0661. RIGGED ACTUATOR IAW MM CHAP 27-11-10. 05 21 2015 09:44:37. CONNECTED THE TEST HARNESS & PITOT & STATIC TEST EQUIPMENT. MOVEMENT CHECKS ARE GOOD. REMOVED THE TEST HARNESS. PERFORMED THE OPERATIONS CHECKS OF THE ROLL RATIO ACTUATOR & OPERATION CHECKS ARE GOOD. INSTALLED THE BELLY ACCESS PANEL. DURING TESTING OF THE TCAS SYS FOR BELLY ANTENNA, NOTED THE ROLL SYS LISTED IN THE NO TAKEOFF BOX. NOTED NO ROLL SYS CONTROL CAS MSG. DISPLACED THE BELLY PANEL & NOTED PROPER POSITION OF THE TARGET PROXIMITY SWITCH. THE PROXIMITY SWITCH IS FAULTY. REMOVED THE PROXIMITY SWITCH ASSEMBLY PN 6908272-12 & SN A61549. INSTALLED NEW PN 6908272-12 & SN A61905. RIGGED & SAFTIED THE SWITCH. RECONNECTED THE TEST EQUIPMENT & RETESTED. OPERATIONS CHECKS ARE GOOD. CYCLED POWER & MONITORED DURING FURTHER MX & NOTED NO MSGS POSTED. REMOVED TEST EQUIPMENT & CLOSED BELLY PANEL ACCESS. OPERATIONS CHECKS OF THE BELLY ANTENNAS ARE GOOD. WORK PERFORMED IAW MM 27-11-10, 05 21 2015 10:24:36.
DURING GEAR RETRACTION, ALL FOUR GEAR LIGHTS EXTINGUISHED NORMALLY, BUT WITHIN 1-2 SECONDS, RED UPLOCK LIGHT FLICKERED & THEN STAYED ON. GEAR EXTENDED NORMALLY. JACKED AIRCRAFT, CONNECTED HYD AND CYCLED GEAR. UNLOCK WOULD REMAIN ON, ON THE FIRST TIME THE GEAR WAS CYCLED, AND THEN OPERATE PROPERLY AFTER THAT. AIRCRAFT WOULD HAVE TO SIT FOR SEVERAL MINUTES AND THEN WOULD FAIL ON FIRST CYCLE. CHECKED CDMS, SAW NLG NOT UP AND LOCKED MESSAGE ON THE PCB 2 PAGE WHILE THE UNLOCK LIGHT WAS ON. THE PCB 1 MESSAGE SHOWED UP/LOCKED WHILE THE UNLOCK LIGHT WAS ON. INSPECTED GEAR WELL WIRING FOUND BOOT ON WIRING GOING TO UP LOCK SWITCH TO BE SPLIT. REMOVED BOOT AND INSPECTED WIRING AND FOUND WIRES CHAFED AND ONE WIRE BROKEN. REPAIRED WIRING FOR NOSE UPLOCK SWITCH AT CONNECTOR IAW MM 20-20-00. INSTALLED NEW WIRING AND CONNECTOR BOOT. CYCLED GEAR SEVERAL TIMES WITH NO FAULT. OPS CHECKED GOOD.
AS THE FLYING PILOT, SMELLED SMOKE AND SAW FLAGS ON THE STNDBY ATTITUDE INDICATOR. MY PARTNER SAW IT AT THE SAME TIME AND TURNED OFF THE STANDYBY INDICATOR. THAT REDUCED THE SMELL. DEPLOYED THE MASKS AND DIVERTED. VERIFIED ATTITUDE INDICATOR IS INOPERATIVE AND SMELLS OF SMOKE. REMOVED INDICATOR AND INSTALLED EXCHANGE REPAIRED UNIT IAW MM 34-22-00. OPS CHECKED GOOD.
DURING A SCHEDULED INSPECTION WE WERE PREFORMING A PRODUCT IMPROVEMENT (REPLACEMENT OF DUCT ASSY 6914070-67) WE NOTICED THAT THE HEAT EXCHANGER SIDE PLATE HAD 1 CRACKS ABOUT .40" LONG. A NEW HEAT EXCHANGER WAS INSTALLED. WE PREFORMED A LEAK CHECK ON THE DEFECTIVE UNIT AND FOUND THE CRACKS EXTENDED INTO THE COOLING FIN AREA, WHERE THEY CAN NOT BE SEEN. THIS CONDITION HAS ALSO BEEN REPORTED TO UNDER SCR 651875.
DURING A SCHEDULED INSPECTION, NOTICED THE HEAT EXCHANGER SIDE PLATE HAD THREE CRACKS ABOUT .30 INCH LONG. OPPOSITE SIDE OF THE HEAT EXCHANGER WAS CRACKED IN THREE OF THE FOUR CORNERS. A NEW HEAT EXCHANGER WAS INSTALLED. PREFORMED A LEAK CHECK ON THE DEFECTIVE UNIT AND FOUND THE CRACKS EXTENDED INTO THE COOLING FIN AREA, WHERE THEY CAN NOT BE SEEN.
ON PREFLIGHT WITH APU RUNNING AND AC ON, SMELLED OILY ODOR AND SAW LIGHT SMOKE IN CABIN. WITH BLEED AIR OFF, SMOKE WENT AWAY WITH JUST A LITTLE OIL ODOR. REMOVED L/R APU PANELS, REMOVED INLET TEMP BULB, UNBOLTED INLET AND MOVED UPWARD TO ACCESS APU INLET. REMOVED TAIL TO RUDDER FAIRING/INTAKE. CW BORESCOPE OF APU INLET, PUT PIC ON FLASH DRIVE. APU INLET AND COMPRESSOR AREA INLET VERY OIL COVERED 9-22-12. RECORDED APU TIME: 3025.5, CYCLES: 4936. REMOVED APU FROM AIRCRAFT. RECEIVED PROVIDED APU. TRANSFERED COMPONENTS, OK TO INSTALL REPLACEMENT APU. INSTALLED APU IAW MM CH 49-10-00. OK TO INSTALL START/GEN RUN AND LEAK CHECK GOOD. OK TO CLOSE APU PANELS. CLOSED PANELS.
RIGHT MLG LIGHT WOULD NOT ILLUMINATE. FOLLOWED THE CHECKLIST PROCEDURE. RESET GEAR SYS IAW MM 32-00-00, BLED SYS. RESERVICED N2 BOTTLE AND SAFETIED. GEAR SWING CHECKED GOOD.
AFTER TAKEOFF, GEAR WOULD NOT RETRACT. A SHORT TIME LATER WE GOT THE AMBER "WOW MISCOMPRE" CAS MESSAGE. ALL CBS ARE SET.
AFTER TAKEOFF, ATTEMPTED TO RAISE GEAR. HANDLE MOVED TO THE UP POSITION, BUT THE GEAR REMAINED EXTENDED. NO OTHER INDICATIONS PRESENT - NO CAS MESSAGE, NO RED LIGHT, THREE GREEN REMAINED ON, NO AUDIO WARNINGS. HANDLE PLACED TO DOWN POSITION FOR LANDING AND LANDING WAS UNEVENTFUL. SUP: TROUBLESHOT LANDING GEAR CONTROL, C/W LANDING GEAR RETRACT CK GOOD. IAW AMCC REQUEST REMOVED AND REPLACED LANDING GEAR CONTROL WITH A REPAIRED UNIT IAW MM CK 32-30-10, GEAR RETRACT CHECK CHECK GOOD.
LOUD NOISE FROM NOSE WAS HEARD DURING GEAR RETRACTION. NOISE (THUMP) WAS FOLLOWED WITH RED GEAR UNLOCK LIGHT REMAINING ILLUMINATED. GEAR EXTENDED WITH 3 GREEN AND UNLOCK LIGHT EXTINGUISHED. JACKED ACFT AND INSPECTED NLG AND NLG WHEELWELL DUE TO RECENT NLG SERVICING, MX, AND REPEAT WRITE-UP. NO DAMAGE NOTED TO NLG STRUT OR IN NLG WHEEL WELL. CHECK AND RESERVICE NLG STRUT PRESSURES. LOWER CHAMBER PRESS 90 PSI; UPPER CHAMBER WAS 260 PSI. COMPLIED WITH COMPLETE NG STRUT SERVICING, HYD FLUID AND NITROGEN, IAW MM CH 32-20-00, TASK 32-20-00 600. DOWNJACKED ACFT STRUT EXTENSION WITHIN LIMITS IAW MM 32-00-00. SET UPPER CHAMBER PRESS TO 280 PSI. SET LOWER CHAMBER PRESS TO 40 PSI.
ON GEAR RETRACTION, NOSE GEAR MADE A NOTICEABLE CLUNK AND BANG AND THE RED GEAR UNLOCK LIGHT REMAINED ILLUMINATED. JACKED AIRCRAFT AND CHECKED FOR PLAY IN NLG AND FOUND NLG TO BE FREE OF EXCESSIVE PLAY. CHECKED UPPER AND LOWER BARREL PRESSURES AND FOUND LOWER BARREL TO BE UNDER PRESSURE BY 10 PSI. SERVICED LOWER BARREL TO THE PROPER PRESSURE AND CHECKED FOR PROPER STRUT EXTENSION GOOD. PER MANUFACTURER TEAM FOUND NLG SQUAT SWITCH SLIGHTLY OUT OF RIG. ADJUSTED AND CHECKED GOOD. DATA REFERENCE. CE-680 M/M 32-60-00/32-20-00.
UPON GEAR RETRACTION, A THUMPING NOISE WAS COMING FROM THE NOSEWHEEL COMPARTMENT ALONG WITH A FLASHING RED UNLOCK LIGHT. PERFORMED SEVERAL GEAR RETRACTIONS AND EXTENSIONS. SERVICED UPPER AND LOWER BARREL (STRUT) PRESSURES. ALL SYSTEMS OPS CHECK GOOD. IAW MM CH 32-20-00.