N535QS
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
JUST BEFORE LANDING WE HAD A CABIN DOOR OPEN CAS MESSAGE. WHILE ON THE GROUND WE TRIED TO RESET IT USING THE PROCEDURE IN THE QRH. STEP FOUR WAS UNSUCCESSFUL, WE COULD NOT GET THE CHECK HANDLE /PUSH TO OVERRIDE LIGHT TO FLASH. : REMOVED AND REPLACED NC105 CABIN DOOR MONITOR PCB PER AMM 24-60-40. OPS CHECKS GOOD NO FURTHER ACTION REQUIRED.
AFTER LANDING LINE TECH INFORMED US THAT LEFT MAIN WAS SMOKING. FOUND SMOKE COMING FROM LEFT MAIN. REPLACED BRAKE TOP BLEED FITTING. OPS CHECK GOOD. IAW MM 32-48-00
33-50-04 RIDE SIDE OVERWING EMERGENCY EXIT LIGHT DOES NOT ILLUMINATE DURING TEST OR ANY OTHER MODE WHEN IT SHOULD BE ILLUMINATED. R & R RT OVERWING EMERGENCY LIGHT IAW AMM 33-50-20. OPS CHECKED GOOD.
ODORS IN COCKPIT / CABIN: REPEAT WRITEUP. WE DEPARTED KIAD AND CLIMBED TO 3000FT. AT LEVEL OFF, WE TURNED ON THE ENG AND WING ANTI ICE. AS SOON AS WE TURNED ON THE ANTI ICE, WE NOTICED AN UNUSUAL ODOR, SORT OF LIKE A PLASTIC FUME TYPE OF ODOR. WE ELECTED TO RETURN TO KIAD AND THE SMELL REMAINED UNTIL APPROXIMATELY 2000FT. AT 2000FT, WE HAD TURNED THE ANTI ICE OFF. PERHAPS THE ANTI ICE IS ASSOCIATED, OR PERHAPS IT WAS COINCIDENCE, BUT IT DID SEEM TO COINCIDE WITH THE ANTI ICE. CORRECTIVE ACTION: PERFORMED INSPECTION OF ANTI-ICE TUBE. NO DEFECTS NOTED. OPS CHECK GOOD. IAW EMM 72-30-01.
ON CLOMB OUT AT 7-8K FT, A BURNING SMELL STARTED . THE ENTIRE FLIGHT THE BURNING SMELL CAME IN STRONG WAVES. THE STRONGEST WAS DURING THE DECENT OUT OF 18K FT AND BELOW . REPLACED ENGINE HP VALVE SEALS. OPS CHECK GOOD. IAW CE-680A AMM 36-10-05
LANDING GEAR HANDLE: AFTER TAKEOFF LANDING GEAR HANDLE WOULD NOT COME OUT OF LOCK DETENT AND GEAR WOULD NOT RETRACT. AFTER LEVELING OFF AT 4000 AND TRYING SEVERAL MORE TIMES GEAR FINALLY RETRACTED WITHOUT ISSUE. NO CAS MESSAGES WERE PRESENT. GEAR EXTENDED ON LANDING WITHOUT ISSUE. REMOVED LANDING GEAR MODULE & INSTALLED NEW LANDING GEAR MODULE IAW AMM 32-30-30.0PS CHECK GOOD AT THIS TIME.
WHEN BRAKING AFTER LANDING THERE IS A LOUD CHATTERING FROM THE BRAKES AND A VERY NOTICABLE VIBRATION AND SHUDDERIG THAT ACCOMPANIES RHE NOISE. WE CAN NOT TELL WHICH MAIN BRAKE IS CAUSING THE PROBLEM. BLED BRAKES AND FOUND A GOOD AMOUNT OF AIR IN THE SYSTEM. TECHS PERFORMED ENGINE RUN AND TAXI FOR OPERATIONAL CHECKS AND LEAK CHECKS. ALL CHECKED GOOD. ALL WORK COMPLETED IAW CE680A AMM 32-42-00 AND 71-00-00
WORN BRAKES: UPON LANDING, WHEN BRAKES APPLIED, HEARD EXCESSIVE SCREECHING AND FELT A SHIMMY COMING FROM BOTH MAINS. . ARRIVED ONSITE AND GAINED ACCESS TO THE AIRCRAFT. PERFORMED GVI OF GEAR, BRAKES AND TIRES WITH NO DEFECTS NOTED. SET BRAKES AND MEASURED WEAR PINS WITH THE FOLLOWING MEASUREMENTS: NR 1, 4/32", NR 2, 4/32, NR 3, 13/32, NR 4, 2/32". DISCUSSED FINDINGS MOC. ADVISED TO MOVE FORWARD WITH BLEEDING ALL FOUR BRAKES TO CHECK FOR ANY AIR IN THE SYSTEM. ALSO ASKED US TO RECORD BRAKE PRESSURED FROM CMC BEFORE AND AFTER BLEEDING TO SEE IF ANYTHING CHANGES. COMPLETED BLEEDING ALL FOUR BRAKES. NO AIR ON EITHER #1 OR #4. ON BRAKES #2 AND #3 WE ONLY NOTED A COUPLE BUBBLES OUT EACH. SERVICED HYDRAULIC RESERVOIR WITH BRAYCO 881AND RESAFETIED ALL FOUR BRAKE FUSES AS REQUIRED PROVIDED MOC WITH PICS FROM CMC OF THE PRESSURED BEFORE AND AFTER BLEEDING, NOT MUCH CHANGE NOTED. WE DID NOTE THE #4 BRAKE HAS HIGHER PRESSURE THAN THE OTHER THREE. WE JACKED BOTH SIDES AND SPUN THE WHEELS WITH NO DRAG NOTED. LINE SERVICE ADVISED THE CREW IS HERE MAYBE THEY COULD PERFORM HIGH-SPEED TAXI CHECK. REACHED OUT TO MCC AND LET THEM KNOW THE CREW IS ONSITE. STEVE AT MCC IS GOING TO TRY AND CONTACT THE CREW AND SEE IF THEY ARE AVAILABLE TO PERFORM A HIGH-SPEED TAXI CHECKS. MCC ADVISED THAT THE CREW IS NOT AVAILABLE TO PERFORM HIGH-SPEED TAXI CHECK. TECHS WILL PERFORM EXTENDED NORMAL TAXI CHECKS TO CHECK FOR ABNORMAL NOISE OR VIBRATION. TAXIED AIRCRAFT FROM FBO TO ACTIVE RUNWAY AND BACK TO FBO. MADE MULTIPLE TRIPS AROUND APPLYING BRAKES AT VARIOUS PRESSURED WITH NO DEFECT NOTED. DISCUSSED FINDINGS WITH MCC AND MCC ADVISED TO MOVE FORWARD WITH RELEASE. WORK DONE WITH REFERENCE TO AMM 32-42-00.
EMERGENCY OVERWING EXIT LIGHT INOP. (PRE-FIGHT) REMOVED AND REPLACED OVERWING EMERGENCY EXIT LIGHT OPS CHECK GOOD WORK DONE IAW CE 680A MM 33-50-20.
BLENDIED 3 AREAS OF CORROSION UNDER AND AROUND NUTPLATES ON PANEL 144CBC MOUNTING FRAME, FOUND AN ADDITIONAL 21 AREAS. BLENDED ADDITIONAL 21 AREAS. NDT VERIFIED CORROSION REMOVAL AND REMAINING THICKNESS. EVALUATED NDT FINDINGS. REPAIRED BLENDED AREAS WITHIN LIMITS PER CESSNA 680A SRM 51-70-03. REPAIRED BLENDED AREAS BEYOND LIMITS PER REPAIR; RFTS-107692 REV.0.
BLENDING 12 AREAS OF CORROSION UNDER AND AROUND NUTPLATES ON PANEL 166AR MOUNTING FRAME, FOUND AND BLENDED AN ADDITIONAL 3 AREAS. BLENDED ADDITIONAL 3 AREAS. NDT VERIFIED CORROSION REMOVAL AND REMAINING THICKNESS. EVALUATED NDT FINDINGS. REPAIRED BLENDED (LEVEL 1)AREAS WITHIN LIMITS PER CESSNA 680A SRM 51-70-03. REPAIRED BLENDED, (LEVEL 2) AREAS BEYOND LIMITS PEE REPAIR; RFTS-107692
REPLACED CORRODED RUDDER FAIRING INNER SUPPORT RIB P/N UNKNOWN WITH NEW TEXTRON P/N 6912670-5 PER CESSNA 680A SRM 51-40-05 AND 51-40-11 AND DUNCAN AVIATION PROCESS GPP-0105 REV. 9.
BLENDED AND TREATED CORRODED AREAS ON THE LH AND RH SKINS OF THE HORIZONTAL STABILIZER. INSTALLED AN EXTERNAL DOUBLER ON THE RH UPPER SKIN TRAILING EDGE IAW ENGINEERING REPAIR ORDER.
BLENDED 2 AREAS OF CORROSION UNDER AND AROUND NUTPLATES ON PANEL 134BBC MOUNTING FRAME, FOUND AN ADDITIONAL 6 AREAS. BLENDED ADDITIONAL 6 AREAS. NDT VERIFIED CORROSION REMOVAL AND REMAINING THICKNESS. EVALUATED NDT FINDINGS. REPAIRED BLENDED AREAS WITHIN LIMITS PER CESSNA 680A SRM 51-70-03. REPAIRED BLENDED AREAS UT OF LIMITS PER REPAIR RFTS-107692 REV.0.
BLENDED 5 AREAS OF CORROSION UNDER AND AROUND NUTPLATES ON PANEL 144ABC MOUNTING FRAME, FOUND AN ADDITIONAL 10 AREAS. BLENDED ADDITIONAL 10 AREAS. NDT VERIFIED CORROSION REMOVAL AND REMAINING THICKNESS. EVALUATED NDT FINDINGS. REPAIRED BLENDED AREAS WITHIN LIMITS PER CESSNA 680A SRM 51-70-03. REPAIRED BLENDED AREAS BEYOND LIMITS PER REPAIR RFTS-107692 REV.0.
BLENDED 6 AREAS OF CORROSION UNDER AND AROUND NUTPLATES ON PANEL 144BBC MOUNTING FRAME, FOUND AN ADDITIONAL 6 AREAS. BLENDED ADDITIONAL 6 AREAS. NDT VERIFIED CORROSION REMOVAL AND REMAINING THICKNESS. EVALUATED NDT FINDINGS. REPAIRED BLENDED AREAS WITHIN LIMITS PER CESSNA 680A SRM 51-70-03. REPAIRED BLENDED AREAS BEYOND LIMITS PER REPAIR RFTS-107692 REV.0.
MAIN DOOR: LIFT BUTTON ON THE INTERIOR DOOR PANEL FOR THE MAIN ENTRY DOOR ONLY WORKS INTERMITTENTLY // SIGNOFF// REMOVED ANDREPLACED DOOR LIFT PANEL IAW CE-680A IMM 25-20-36-01 OPS CHECK GOOD
WOW MISCOMPARE AMBER CAS: WOW MISCOMPARE MESSAGE ON SHORT FINAL. WENT AROUND. UPON GEAR RETRACTION, GEAR STAYED DOWN AND GESR DISAGREE LRN MESSAGE APPEARED. RAN CHECKLIST. AFTER PUTTING GEAR HANDLE DOWN GEAR MESSAGE WENT AWAY. FOLLOWED A MINUTE OR TWO LATER BY WOW MISCOMPARE MESAGE CLEARING. LANDED NORMALLY PWK.
RECEIVED THE EMERGENCY POWER SUPPLY PACKS. GAINED ACCESS AND REMOVED #1 EMERGENCY POWER SUPPLY PACKS PN: CBS28-1, SN: 3533M DUE TO INTERNAL FAILURE. INSTALLED REPAIRED EMERGENCY POWER SUPPLY PACKS PN: CBS28-1, SN: 005693. GAINED ACCESS AND REMOVED #2 EMERGENCY POWER SUPPLY PACKS PN: CBS28-1, SN: 005362 DUE TO INTERNAL FAILURE. INSTALLED REPAIRED EMERGENCY POWER SUPPLY PACKS PN: CBS28-1, SN: 006280. GAINED ACCESS AND REMOVED #3 EMERGENCY POWER SUPPLY PACKS PN: CBS28-1, SN: 008393 DUE TO INTERNAL FAILURE. INSTALLED REPAIRED EMERGENCY POWER SUPPLY PACKS PN: CBS28-1, SN: 006281. GAINED ACCESS AND REMOVED #4 EMERGENCY POWER SUPPLY PACKS PN: CBS28-1 , SN: 005406 DUE TO INTERNAL FAILURE. INSTALLED REPAIRED EMERGENCY POWER SUPPLY PACKS PN: CBS28-1, SN: 005602. PERFORMED EMERGENCY LIGHT OPS CHECK AND OPS CHECK WAS SATISFACTORY. CLOSED ACCESS AND RETURNED THE AIRCRAFT TO ITS ORIGINAL CONFIGURATION. WORK WAS DONE IRW CE-680A AMM 33-50-06. 21 FEB2022. PARTS:
EMERGENCY LIGHTS BATTERY: LAV EMER OVERHEAD LIGHT & FLOOR LIGHTS ARE DIM // SIGNOFF// COMPLIED WITH NJA TASK CARD TC-FLT-33-1001 CESSNA CE-680A EMERGENCY LIGHTING POWER SUPPLY BATTERY EXCERCISE PROCEDURE (REV.0, DATED: 15-DEC-2021) ALL EMERGENCY LIGHTS OPERATE CORRECTLY WITH NO DEFECTS NOTED.
RH MLG AXLE PLATING DAMAGE (CHIPPED). ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DQ32824M1 DATED DECEMBER 10, 2021; 680A-0078 (N535QS) RIGHT MAIN LANDING GEAR AXLE PLATING DAMAGE (CHIPPED).
REPAIR OF RIGHT MAIN LANDING GEAR AXLE PLATING DAMAGE. TEXTRON AVIATION ENGINEERING REPAIR LETTER DQ32824M1 DATED: DEC. 10, 2021, 680A-0078 (N535QS) RIGHT MAIN LANDING GEAR AXLE PLATING DAMAGE (CHIPPED).
CRACK DAMAGE, NOSE LANDING GEAR WHEEL WELL (NWW), FRAME, WEB, AND DOUBLERS, FS 75. ACCOMPLISHED TEXTRON AVIATION FIELD REPAIR SR-680A-ATA53-25890 REV- DATED JUNE 1, 2020 AND 8100-9 DATED 6/1/2020; STANDARD REPAIR - CRACK DAMAGE, NOSE LANDING GEAR WHEEL WELL (NWW), FRAME, WEB, AND DOUBLERS, FS 75.
AT FL 430 HEAVY BANGING / VIBRATION COMING FROM NOSE WHEEL AREA WITH RAPID CONCESSION. NO CASS MESSAGES. NO GEAR ERROR INDICATION OTHER THAN UP. BELOW 16000 AND 210 KNOTS BANGING / VIBRATION WENT AWAY. NORMAL GEAR EXTENSION WITH DOWN LOCKED INDICATIONS. HAD AIRCRAFT TOWED TO PARKING. REPACKED NLG STRUT AND REASSEMBLED NLG STRUT LOWER BARREL P/N 6742170-8 IAW CMM 32-20-01. SERVICED NLG STRUT TO SPEC IAW M 12-10-52. OPS CHECK GOOD LANDING GEAR SWINGS ACCOMPLISHED THE NOSE STEERING ISOLATION VALVE OPERATIONAL CHECK PER MM 32-50-00-05, WHILE DOING THE CHECK APPLIED COLD SPRAY TO THE VALVE, NO DEFECTS NOTED. ACCOMPLISHED THE NOSE AND MAIN GEAR UPLOCK SWITCH ADJUSTMENT PER MM 32-32-00-05, NO DEFECTS NOTED, NOSE SWITCH MEASURED .18", LT GEAR SWITCH MEASURED .23", RT GEAR SWITCH MEASURED .18", ALL ARE WITHIN TOLERANCE. VERIFIED ISOLATION VALVE OPERATIONAL CHECK. VERIFIED UPLOCK SWITCH ADJUSTMENT CHECK GOOD. OPERATIONALLY CHECKED UPLOCK SWITCHES BY EXTENDING EACH GEAR INDIVIDUAL AND APPLY HYDRAULIC PRESSURE. EACH LANDING GEAR RETRACTED AND INDICATED UP AND LOCKED, VIEWED DATA AND FOUND THAT NOSE GEAR IS BUMPING RAPIDLY WITH NO INDICATION OF EITHER MLG BUMPING. WHILE MONITORING THE NC106/NF206 PCB'S THE NOSE GEAR UPLOCK CHANGES FROM UP AND LOCKED TO NOT UP AND LOCKED RAPIDLY. THE RETRACTING INDICATION ALSO CHANGES FROM STATIC TO IN MOTION. ALSO MONITORED GSD NR 3 FOR NOSE GEAR UPLOCK INDICATION AND FOUND THAT IT SHOWED UP AND LOCKED DURING THE ENTIRE TIME GEAR BUMP OCCURRED. WITH GEAR RETRACTED AND HYDRAULIC PRESSURE APPLIED, TRIED SHAKING NOSE GEAR TO INDUCE GEAR BUMP BUT COULD NOT. ALSO VERIFIED WITH NOSE GEAR UP THE UPLOCK HOOK IS NOT RESTRICTED FROM FULL FWD ENGAGEMENT REMOVED AND REPLACED NOSE LANDING GEAR UP LOCK SWITCH P/N S3177-1 IAW MAINTENANCE MANUAL 32-32-10 COMPLIED WITH LANDING GEAR UP LOCK ADJUSTMENT TEST IAW MM 32-32-00 COMPLIED WITH LANDING GEAR OPERATIONAL CHECK IAW MM 32-00-00 VERIFIED REPLACEMENT AND FUNCTION CHECK OF NOSE LANDING GEAR UPLOCK SWITCH RANG GNCS03 TO THE SG006 SWITCH PIN 1, AND FROM PIN 2 AND 5 TO THE PCB PIN 52 ON .NC106 AND NF206 PER TEAM. ALL CHECKED GOOD. ACCOMPLISHED GEAR SWINGS AFTER WIRE CONTINUITY CHECK. OPS CHECK GOOD. NLG REPACK KIT P/N CPD680-32-4 WAS USED. PER CUSTOMER REQUEST, REPLACED HYDRAULIC MANIFOLD. CORRECTION TO ABOVE STATEMENT: "PER CUSTOMER REQUEST, REPLACE HYDRAULIC MANIFOLD. GAINED ACCESS AND REMOVED LANDING GEAR HYDRAULIC MANIFOLD PN: 9914649-5 SN: 0927 IAW AMM 32-30-20. INSTALLED NEW LANDING GEAR HYDRAULIC MANIFOLD P/N 9914649-5 S/N 0906 IAW MM 32-30-20. ACCOMPLISHED LEAK CHECK AND LANDING GEAR OPERATIONAL CHECK IAW MM 32-00-00. LEAK AND OPS CHECK GOOD. ACCOMPLISHED LANDING GEAR EMERGENCY EXTENSION FUNCTIONAL CHECK IAW MM 32-34-00. GEAR EMERGENCY BOTTLE NEEDS SAFETIED AND SERVICED. A/C REQUIRES FULL HYDRAULIC BLEEDING. SERVICED GEAR BLOW DOWN BOTTLE AND SAFETIED IAW MM 12-10-45. ACCOMPLISHED FULL HYD SYSTEM BLEED IAW MM 12-10-30 VERIFIED NOSE AND MAIN LANDING GEAR EMERGENCY UPLOCK RELEASE CABLES ARE NOT UNDER LOAD OR RESTRICTING THE UPLOCK HOOK EXTENSION.
CLIMBING THRU FL370 WE HEARD A LOUD NOISE WITH LOUD AND HEAVY VIBERATIONS, CONSTANT PITCH VIBRATIONS WITH OCCASIONAL HARD YAWS TO THE LEFT AND RIGHT... COMING THRU A SINGLE DIGET ALTITUDE THE VIBERATIONS JUST STOPPED.//SIGNOFF//PERFORMED ARES DOWNLOAD, CHECKED RUDDER AND AUTOPILOT MOVEMENT ALL CHECKS GOOD, PERFORMED GEAR SWINGS , FOUND LH GEAR DOOR LOOSE AND NOT STREAMLINE WITH SURFACE, ADJUSTED GEAR DOOR OPS CHECK FIT CHECK GOOD.DONE IAW CE 680A MM 52-80-25. SPOKE WITH TEAM LATITUDE, LOOKING INTO FLIGHT ARES DATA REPORT AND FOUND NO CAS MESSAGES, NO ERRONEOUS YAW INPUTS/OUTPUTS DURING THE WINDOW THE PILOTS SAID THEY HAS EXCESSIVE LEFT AND RIGHT YAW, NO ISSUES TO REPORTED DURING FLIGHT DURING THE ENTIRE FLIGHT
WING ANTI ICE CROSS FLOW VALVE STUDS HAVE DAMAGED LOWER FUSELAGE SKIN IN TWO PLACES. BLENDED, OUT DAMAGE TO PREPARE FOR NDT. NO CRACKS NOTED. COMPLETED STANDARD REPAIR SR-680A-ATA53-22175.
WING ANTI-ICE CROSSFLOW VALVE HAS CAUSED DAMAGE TO THE LOWER FUSELAGE SKIN. DURING INSPECTION FOUND THERE IS A CHAFFED SPOT ON THE LOWER SKIN P/N: 7411392-12 OF SKIN BOND ASSEMBLY P/N: 7411391-2 FROM A STUD PROTRUDING FROM THE ANTI-ICE CROSS FLOW VALVE THAT HAS RUBBED INTO THE SKIN. THE AFFECTED AREA IS APPROXIMATELY 1/8" ROUND. BLENDED THE AREA AND NDT'D FOR CRACKS. NO CRACKS NOTED. THICKNESS MAPPED AS REQUIRED. DEPTH AT THIS TIME IS .002" DEEP. BLENDED DAMAGE AREAS IAW SRM 51-70-03 AND INSTALLED 0.040" SHIM IAW LETTER DQ22111M2 DATED 07/08/2019.
PRI STAB TRIM FAIL EICAS AMBER MESSAGE IN FLIGHT. PERFORMED THE APPROPRIATE QRH CHECKLIST, FOLLOWED BY THE EMERGENCY/ABNORMAL PROCEDURES, FLAPS NOT IN LANDING POSITION // SIGNOFF // REMOVED THE PRIMARY STAB TRIM ACTUATOR AND INSTALL A NEW SERVCEABLE PRIMARY STAB TRIM ACTUATOR ACCOMPLISHED FOLLOW ON CHECKS AS REQUIRED OPERATIONAL CHECKS GOOD. CLOSED ACCESS AS REQUIRED MAINTENANCE ACOMPLISHED IAW AMM CH. 27-40-05 AND 27-40-00.
NR 2 FMS WENT BLANK AND A ELECTRICAL BURNING ODOR WAS NOTICED SHORTLY AFTERWARDS IN COCKPIT. REPLACED NR 2 FMS IAW HAWKER 1000 AMM CHAPTER 34-61-00, OPS CHECK GOOD IAW HAWKER 1000 AMM CHAPTER 34-61-00.
FUEL FEED LINE FOR APU FOUND DURING INSPECTION. OUTSIDE FUEL SLEEVEING HAD 2 HOLES BURNED THROUGH. FIRE RETARDANT SLEEVE HAD ONE HOLE BURNED IN RED RUBBER COVERING. WAS NOT BURNED TO HOSE AT THIS TIME.