N642QS
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
BRAKE PRESSURE LIGHT: WHILE HOLDING SHORT OF RUNWAY AMBER ANTI SKID ANNUCIATOR ILLUMINATED AND POWER BRAKE CIRCUIT BREAKER TRIPPED. CALLLED MAINTENACE DID ONE RESET AND TOLD TO NOT TAKEOFF . BACK TAXIING RUNWAY 10 LOST POWER BRAKES AND LOW BRAKE PRESS LIGHT ILLUMINATED AND USED EMER BRAKE HANDLE TO STOP IMMEDIATELY CALLED UNICOM THAT WE WERE DISABLED ON RUNWAY AND THEY MADE ANNOUNCEMENTS ON UNICOM AND PROMPTLY SENT A TUG OUT TO TOW US IN. ON POST FLIGHT INSPECTION THERE WAS NO HYDRAUIC LEAKS OBSERVED AND BRAKE FLUID RESERVOIR WAS FULL CORRECTIVE ACTION: REPLACED HYDRAULIC PACK ASSY. OPS CHECK GOOD. IAW CESSNA 560XL AMM 32-44-00
FORWARD CABIN EMERGENCY LIGHTS ARE INOP. REPLACED FWD EMERGENCY BATTERY PACK. OPS CHECK GOOD. IAW CE-560XL MM 33-50-01.
LEFT FUEL TRANSFER: WHILE AT FL400, FUEL CROSSFEED WAS SELECTED FROM L TANK TO R ENG. THE FUEL XFEED AND FUEL BOOST L ANNUNCIATED AS NORMAL. SHORTLY THEREAFTER WE RECEIVED A MASTER CAUTION WITH FUEL BOOST R ANNUCIATOR. THE CROSSFEED WAS THEN SELECTED OFF AND BOTH L AND R FUEL BOOST REMAINED ON. WE THEN ACCOMPLISHED THE QRH FOR FUEL BOOST L OR R. THE BOOST PUMPS WERE SELECTED ON THEN BACK TO NORM POSITION. WE DID THIS SEPERATELY FOR EACH BOOST PUMP AND THE ANNUNCIATORS CLEARED. CORRECTIVE ACTION; PERFORMED SATISFACTORY OPS CHECK OF FUEL TRANSFER SYSTEM. WAS NOT ABLE TO DUPLICATE FAULT. GAINED ACCESS TO AND SWAPPED LEFT AND RIGHT FUEL PCB BOARDS REMOVED AND REPLACED XFEED ACTUATOR. OPS CHECK OK. NO FURTHER DEFECTS NOTED. WORK PERFORMED IN ACCORDANCE WITH CE560XL AMM 28-21-06.
MLG BRAKE PRESSURE: DURING TAXI, LOST ALL BRAKE PRESSURE AT THE PEDALS FOR ABOUT 5-10 SECONDS. BRAKE PRESSURE RETURNED AND BROUGHT AIRCRAFT TO STOP. HAD AIRCRAFT TUGGED TO RAMP. NO LEAKS NOTED AT BRAKES. BRAKE RESERVOIR AND ACCUMULATOR NORMAL. NO BREAKERS POPPED. NO ABNORMAL ANNUNCIATIONS.//CORRECTIVE ACTION//INSPECTED THE BRAKE RESERVOIR AND ACCUMULATOR PRESSURE AND FOUND IT TO BE CORRECTLY SERVICED AS STATED BY CREW. COMPLETED OPERATIONAL CHECKS OF THE MOTOR AND PUMP AND FOUND NO FAULTS. PUMP TURNS ON AND OFF AT THE CORRECT PRESSURES. GAINED ACCESS TO THE BRAKE METERING VALVE AND CONFIRMED THAT EACH BRAKE PEDAL WAS ACTUATING THE CORRECT METERING VALVE INPUT. INSPECTED BRAKE ASSEMBLIES FOR ANY OBVIOUS ISSUES AND FOUND NONE. COMPLETED BRAKE BLEEDING PROCEDURE AND MADE SURE THERE WAS NO BRAKE CHATTER AND NO AIR BUBBLES IN THE RESERVOIR DURING THE BLEEDING PROCEDURE. ALSO CONFIRMED BRAKE PRESSURE AT THE BRAKE ASSEMBLIES. COMPLETED TAXI CHECKS WITH NO FAULTS. SPOKE WITH MCC AND INFORMED THEM OF OUR FINDINGS AND THEY SAID NO FURTHER ACTION IS REQUIRED. WORK DONE WITH REFERENCE TO CE560XLS AMM 32-44-00
MAIN DOOR HANDLE: MAIN DOOR HANDLE REQUIRES EXCESSIVE FORCE TO OPEN AND LOCK FROM INSIDE OF CABIN. /// SIGN OFF /// PERFORMED GVI OF MED AND FOUND VERY DIRTY DOOR PINS. CLEANED AND LUBRICATED DOOR PINS. DOOR OPS CHECKED GOOD. ALL WORK DONE IAW CE-560XLS AMM CHAPTER 52-10-01.
FLOOR EMERG EXIT LIGHT: DROP ISLE EMERGENCY LIGHT STRIP UNDER MAIN CABIN ENTRY DOOR ILLUMINATES OFF AND ON WITH EMER LTS SWITCH IN ON POSITION. APPEARS THE LIGHTING STRIP CONNECTION IS LOOSE // REMOUNTED LIGHT STRIP OPERATIONAL CHECK WAS FOUND TO BE SATISFACTORY REF CE560 XL MM 33-50-00
CABIN EMERG LIGHT: FRONT HALF OF EMERGENCY LIGHTS IN THE CABIN NOT WORKING THE EXIT LIGHT, FLOOR LIGHTS IN, OVERHEAD LIGHTS ON INITIAL PREFLIGHT. AFTER COLD SOKE PROCEDURE TR 21-04 APU RAN GOR 30 MINUTES LIGHTS CAME ON BRIEFLY FOR LESS THAN 20 SECONDS AND THEN WENT OUT THE EXIT LIGHT FLOOR LIGHTS. THE OVERHEAD LIGHTS WERE VERY DUMB // SIGNOFF// COMPLIED WITH TC-5XL-33-191202 (CE560XLS EMERGENCY LIGHTING BATTERY PACK REPLACEMENT - POST INSTALLATION TASKS IAW NETJETS TC-5XL-33-191202 DATED 1/29/2020.
MAIN CABIN DOOR EXTERIOR DOOR HANDLE. WHEN CLOSING THE MAIN CABIN DOOR FROM INSIDE IT WILL NOT MOVE THE EXTERIOR DOOR HANDLE, STICKS OUT. // SIGNOFF// REMOVED AND REPLACED MAIN CABIN DOOR EXTERIOR DOOR HANDLE SPRING P/N SL5204-2 WITH A CUSTOMER SUPPUED NEW PART. PERFORMED SATISFACTORY OPERATIONAL CHECKS OF MAIN CABIN DOOR EXTERIOR HANDLE. EXTERIOR HANDLE MOVING AND STOWING WHEN CLOSING DOOR WITH INTERIOR HANDLE,
MAIN DOOR VISUAL INDICATOR: MAIN DOOR HANDLE FLAG INDICATES LOCKED WHEN DOOR IS UNLOCKED, AND INDICATES UNLOCKED WHEN DOOR IS LOCKED. REMOVED. THE MAIN DOOR STEPS TO GAIN ACCESS TO THE HAND FLAG INDICATOR. REPOSITIONED THE MAIN DOOR HANDLE FLAG LNDI.CATOR IAW CE~56QXLS SPM 20-10-65. REINSTALLED THE MAIN DOOR STEPS IAW CE-560XLS AMM 52-10-02: OPERATIONAL CHECK OF THE FLAG INDICATORS IS GOOD ATTT,
FOUND THE UPPER TRAILING EDGE EXTRUSION ON THE RUDDER TO BE CORRODED BEYOND LIMITS. REPLACED UPPER TRAILING EDGE EXTRUSION WITH NEW CESSNA PN 5533000-30. PAINTED AND BALANCED RUDDER AS REQUIRED.
MAIN DOOR, HANDLE WILL NOT OPEN MAIN DOOR FROM THE OUTSIDE OR INSIDE WITHOUT PUSHING THE PRECATCH RELEASE BUTTON. SIGN OFF. REMOVED MAIN ENTRY DOOR ALT TRIM PANEL TO ACCESS THE MAIN CABIN DOOR ACOUSTIC SEAL INFLATION VALVE. REMOVED THE STICKING ACOUSTIC SEAL INFLATION VALVE AND INSTALLED A NEW CUSTOMER SUPPLIED INFLATION VALVE. OPERATIONS AND LEAK CHECKS GOOD. MAIN CABIN DOOR ACOUSTIC SEAL NOW FULLY DEFLATES IN 4 SECONDS. CLOSED ACCESS. WORK DONE, IAW CESSNA CE-S60XL AMM 52-10-04. NO DETECTS NOTED AT THIS TIME.
RIGHT WING UPPER SKIN FILLER CORROSION ENGINEERING LETTER DQ27848M1.
LT NOSE SKIN CORROSION ENGINEERING LETTER DQ27848M1.
RT NOSE SKIN CORROSION ENGINEERING LETTER DQ27848M1.
LEFT STUB WING SKIN STRAP CORROSION ENGINEERING LETTER DQ278850.
CABIN SPADE DOOR CORROSION ENGINEERING LETTER DQ278849.
FOUND CRACK ON LOWER TRAILING EDGE OF RUDDER TRIM TAB. FABRICATED AND INSTALLED DOUBLER ON RUDDER TRIM TAB LOWER TRAILING EDGE. WORK ACCOMPLISHED IAW AQRD ERO-965397 DATED 12-11-19 AND 8110-3 DATED 12-11-19
MED HAS ONE CRACK EACH ON THE FWD & AFT WEB ASSY. EACH CRACK MEASURES APPROXIMATELY 0.25 INCHES LONG. ACCOMPLISHED MAJOR REPAIR IAW ERO-886507 DATED FEB 23/2017 & FAA FORM 8110-3 DATED FEB 23/2017.
DESCENDING THROUGH APPROXIMATELY FL 340 GOT PITCH TRIM ANNUNCIATOR. DISENGAGED AUTOPILOT & REALIZED IT WAS A JAMMED ELEVATOR TRIM. RAN CHECKLIST WHILE MAKING DECENT TO LOWER & WARMER ALTITUDE. AFTER LEVEL AT 4000 FEET FOR APPROX FIVE MINUTES ELEVATOR TRIM UNJAMMED & OPERATED NORMALLY. VISUALLY INSPECTED ELEVATOR TRIM CABLES IN HORIZONTAL STABILIZER & EMPENNAGE, NO DEFECTS NOTED AT THIS TIME. LUBRICATED LT & RT ELEVATOR TRIM TAB ACTUATORS WITH PN GREASE 5565450-28 IAW AMM, CHAPTER 12-21-01. OPERATED SYS 4 FULL CYCLES BY HAND & 4 FULL CYCLES WITH ELEC TRIM & OPERATIONAL CHECKS GOOD AT THIS TIME.
LEFT MAIN BRAKE IS GRABBING WITH MODERATE BRAKE APPLICATIONS. MOST PRONOUNCED AT HIGHER SPEEDS INCLUDING LANDING ROLLOUT. A BINDING NOISE CAN BE HEARD WHEN APPLYING HARDER LEFT BRAKE APPLICATIONS. BLED LEFT AND RIGHT BRAKES AND PERFORMED OPERATIONAL CHECK OF THE ANTI-SKID BRAKE SYSTEM IAW CE-560XL AMM 32-44-00. OPS CHECK GOOD.
LEFT BRAKE GRABBING DURING TAXI AT SLOW SPEEDS, CAUSING THE ACFT TO VIBRATE. FOUND AIR IN BRAKES. BLEED BRAKES IAW MM 32-42-00, PERFORMED TAXI CHECK AND BRAKES CHECKED GOOD.
WITH APU RUNNING ON ENGINE START, CABIN FILLED WITH SMOKE. SHUTDOWN ENGINES AND APU, LATER STARTED APU AND CABIN FILLED WITH SMOKE, APU SHUTDOWN BY ITSELF. STARTED RT ENGINE AND SMOKE CAME INTO CABIN AGAIN, SHUTDOWN RT ENGINE. CHECKED APU OIL AND BOTH LIGHTS WERE ON. REMOVED ACFT APU IAW 49-10-00 MM 3-25-13. SUPPLIED APU INSTALLED. RAN APU , OPS AND LEAK CHECKED GOOD IAW MM 49-10-00 3-20-13. R & R WATER SEPERATOR CLOTH IAW ENVIRONMENTAL CONTROL SYSTEMS MM 4-404 3/26, LEAK CHECKED GOOD.
CLIMBING THRU 18,000' AND JUST TURNED ANTI-ICE OFF, WE HEARD A LOUD BANG FOLLOWED BY MULTIPLE BANGS, WITH VIBRATION AND A MOMENTARY SMELL OF SMOKE THRU THE ENVIROMENTAL SYS. LEFT ENG ITT WAS IN THE RED WITH NO OTHER ENG PARAMETERS NOTED TO BE IN THE RED. WE SHUTDOWN THE ENGINE, DECLARED AN EMERGENCY AND PROCEEDED WITH THE ENG SHUTDOWN CHECKLIST. R & R THE LT ENGINE AND OPS CHECKED IAW MM 71-00-02 AND 71-00-03. OPS AND LEAK CHECKS GOOD.
SHORTLY AFTER A TAKEOFF A VERY PROMINENT GRINDING FEELING COULD BE FELT IN THE YOKE. THIS GRINDING COULD BE FELT DURING THE CLIMB AND AT INTERMEDIATE LEVEL OFF ALTITUDES. THE GRINDING DID NOT SEEM TO DISSIPATE UNTIL WE WERE ON FINAL APPROACH AND AT APPROACH SPEED. GRINDING COULD NOT BE DUPLICATED ON THE GROUND. NOTED COPILOTS CONTROL COLUMN BOOT BINDING. POSITION CLEARANCE, CHECKED GOOD MOVED ELEVATOR CONTROLS THROUGH FULL RANGE. NO DEFECTS NOTED. WORK PERFORMED REF THE MM 27-31-00.
ACM OVERHEAT ANNUNCIATOR ILLUMINATED AFTER TAKEOFF. ABNORMAL CHECKLIST WAS FOLLOWED AND WE RETURNED TO THE AIRPORT. AFTER OBSERVING ANNUNCIATOR, THERE WAS A WARM RUSH OF AIR AND A BURNED ODOR DETECTED WITHIN THE CABIN.
ACM OVERHEAT ANNUNCIATOR ILLUMINATED AFTER TAKEOFF. ABNORMAL CHECKLIST WAS FOLLOWED AND RETURNED TO AIRPORT. AFTER ILLUMINATION OF THE ACM OVERHEAT ANNUNCIATOR, A WARM RUSH OF AIR AND A BURNED ODOR DETECTED WITHIN CABIN. TROUBLESHOT SYS DOWN TO A RESISTIVE TEMPERATURE SENSOR. R & R TEMP SENSOR IAW THE MM 21-51-00. OPS CHECKED OK.
LEFT ENGINE ITT EXCEEDED LIMITS AFTER TAKEOFF. ITT REACHED 800 DEGREES FOR NO MORE THAN 30 SECONDS, AND RETURNED WITHIN LIMITS UPON THROTTLE RETRACTION. DOWNLOADED NR 1 ENGINE DCU, VERIFIED MAX ITT REACHED WAS 725. TURBINE TRACKER SHOWED MAX ITT REACHED 730. BORESCOPED LT ENGINE HOT SECTION COMPONENTS. NO DEFECTS NOTED. PERFORMED 5 POINT RUNS ON LEFT ENGINE, CAPPED AND UNCAPPED. PERFORMED LEAK CHECK OF BLEED LINES INCLUDING P3 LINES. GASKET LEAKING. NO OTHER LEAKS NOTED AT THIS TIME. VERIFIED ACM IS NOT LOCKED AND ROTATES FREELY. FOUND GASKET BETWEEN BOV AND TORQUE MOTOR TO BE BLOWN OUT. REMOVED AND REPLACED GASKET. COMPILED WITH GROUN RUNS AND BOV VALVE OPERATION DURING 5 POINTY RUNS. REMOVED BLEED AIR CAPS AND REINSTALLED BLEEDS AIR LINES.COMPLIED WITH LEAK CHECKS. VISUALLLY INSPECTED ITT THERMOCOUPLE WIRING HARNESS, THERMOCOULE PROBES AND TERMINAL BOSSES, NO DEFCTS NOTED. ACCOMPLISHED THE THERMOCOUPLE INSULATION RESISTANCE AND CONTINUITY CHECKS, NO FAULTS NOTED. ACOOMPLISHED THE INDICATOR AND WIRING HARNESS OPERATIONAL TEST NO FAULTS NOTED AS PER MM 72-20-01. GROUND RAN LEFT ENGINE AT TAKE OFF POWER, NO DEFECTS NOTED.
(EMERGENCY DECLARED) PASSING THRU 10,000 FT, RT WING OVERHEAT LIGHT ILLUMINATED WITH ANTI-ICE SWITCH IN (OFF) POSITION. REDUCED POWER ON RT ENGINE TO IDLE AND LIGHT DIDNâT EXTINGUISH. APPROX 5 MIN LATER WHILE ENROUTE TO LANDING, LIGHT DID EXTINGUISH. LANDED UNEVENTFULLY; AC DID NOT EXCEED MAX LANDING WEIGHT. CHECKED VOLTAGE AND OPERATION OF RT ANTI-ICE VALVE IN ALL POSITIONS. OPS CHECKS GOOD. CHECKED RT ENG PCB, NO DEFECTS NOTED. COMPLIED WITH OPERATIONAL CHECK OF ANTI-ICE SYS. OPS CHECKS GOOD IAW MM CHP 30-11-00
AFTER CROSSFEEDING FROM LEFT OT RIGHT TANK , WHEN CROSSFEED SWITCH IS TURNED OFF ( CENTER ) THE RIGHT LO FUEL PRESS ANNUNCIATOR ILLUMINATES MOMENTARILY, FOLLOWED BY A STEADY R FUEL BOOST ON ANNUNCIATOR. SWITCHING THE RT BOOST PUMP SWITCH TO ON AND BACK TO NORM WILL NOT TURN OFF THE ANNUNCIATOR. APU WAS OFF. REMOVED INTERMITTENT RH MOTIVE FLOW VALVE, P/N 905, S/N 905. INSTALLED AN OVERHAULED UNIT, P/N 4151 SN 644, OVERHAULED BY PNEU DRAULICS, CRS# PD6R469J, UNDER WO# 37694*1. WORK PERFORMED IAW CE-560XL M/M, CHAPTER 28-21-06. OPERATIONAL CHECKS GOOD.
GREEN RT MLG LIGHT ILLUMINATED AFTER GEAR RETRACTION, STAYED ON FOR ABOUT 5-6 MINUTES AND THEN LIGHT WENT OUT, AIRCRAFT WAS COLD SOAKED. THE AIRCRAFT WAS COLD SOAKED THE NIGHT BEFORE. APPROACH AND LANDING RESULTED IN NO ABNORMALITES. REMOVED AND REPLACED RT MAIN LANDING GEAR ACTUATOR IAW CE560XLS MM CH 32-30-04. GROUND CHECKS GOOD.
ON GROUND AT APA, WITH APU RUNNING AND BLEED AIR ON AND AVIONICS ON, SMOKE IMMEDIATLEY FILLED THE COCKPIT AND FRONT PART OF CABIN. FOUND APU OIL OVER SERVICED, DESERVICED APU AND CLEANED WATER SOCK IAW CE 560XL M/M CH 12-19-02. OPS CHECK GOOD, NO SMOKE OR SMELL NOTED. ACCOMPLISHED NETJET JOB CARD FOR XL APU SMOKE IN CABIN, APU LEAK AND OPS CHECKED GOOD IAW CE 560XL MM CHAPTER 49-10-00.
NOSE WHEEL STEERING PIN DISCONNECTED FROM STEERING ASSEMBLY ON TAKEOFF AT 70K. REMOVED AND REPLACED CUT WORN NOSE WHEEL ASSY WITH NEW SERVICEABLE WHEEL ASSY. INSPECTION THE NOSE GEAR ASSY, TORQUE LINKS, TORQUE LINK PIN, AND RETAINING CLIP. FOUND NO DEFECTS NOTED AT THIS TIME ON THE NOSE GEAR ASSY AND ATTACHING PARTS. ALL WORK IAW MM 32-41-01.
AT APPROX FLIGHT LEVEL 1200, LEFT ENGINE FIRELIGHT CAME ON, THROTTLE WAS REDUCED TO IDLE, LIGHT CYCLED ON/OFF. 1ST BOTTLE WAS DISCHARGED AS PER CHECKLIST, LEFT FIRE LIGHT CONTINUED TO CYCLE ON/OFF. 2ND BOTTLE WAS DISCHARGED AS PER CHECKLIST, LIGHT EXTINGUISHED. DID NOT SEE ANY ABNORMAL ENGINE INDICATIONS PRIOR TO ENGINE SHUTDOWN. REPLACED BOTH FORWARD AND AFT FIRE BOTTLES IAW CE560XL M/M CHAP 26-21-01. REMOVED LEFT ENGINE FIRE LOOP, AND INSTALLED NEW LOOP. REMOVED LEFT FIRE DETECTION CONTROL UNIT. ALL DONE IAW CE-560XL MM CHAP 26-11-01 AND CHAP 26-11-02. OPS CHECK SATISFACTORY. RESET ECS BUTTON.