N589QS
Registered owner: NETJETS SALES INC, OK (owner ≠ operator)
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
WHILE CLIMBING OUT WE NOTICED THE NO LIGHT ( NOSE GEAR GREEN LIGHT ) ILLUMINATED . WE RAN THE QRH AND DIVERTED TO MEM. REMOVED SUSPECTED FAULTY LANDING GEAR CONTROL UNIT PN 049801-001 SN L2104 AND INSTALLED REPAIRED LANDING GEAR CONTROL UNIT PN 049801-001 SN 0074 IAW CE-560XL AMM 32-30-01. OPS CHECK GOOD.
UPON LANDING GEAR RETRACTION, THE RED UNLOCK LIGHT STAYED ILLUMINATED. THE HYD PRESS LIGHT STAYED ILLUMINATED AND STARTED FLASHING WITH ASSOCIATED MASTER CAUTION LIGHT. STAB MISCOMPARE LIGHT ALSO ILLUMINATED. EXTENDED GEAR, GOT THREE GREEN AND ALL LIGHTS WENT OUT. ON POST FLIGHT, NO DAMAGE, FOD OR HYDRAULIC ISSUES NOTED HYDRAULIC RES IS FULL. NO HYDRAULIC LEAKS NOTED. CORRECTIVE ACTION: REPLACED PRESSURE SWITCH. OPS CHECK GOOD. IAW CE-560XL AMM 27-40-00.
LEFT HORIZONTAL STAB: AFTER EXTENDING FLAPS TO 15 FOR LANDING, WE RECEIVED A STAB MISCOMP APPROX 1 MIN AFTER THE HYD PRESS HAD BEEN CONTINUISLY ILLUMINATED. THE STAB MISCOMP EXTINGUISHED AND APPROX 1 MIN LATER THE STAB MISCOMP RETURNED A SECOND TIME PRIOR TO GEAR EXTENSION. AFTER RUNNING THE QRH AND PULLING THE STAB CONTROL CB, THE HYD PRESS EXTINGUISHED. //SIGNOFF// REMOVED AND REPLACED FAULTY AIRSPEED SWITCH WITH NEW UNIT IAW CE560XL AMM 27-40-00, LEAK AND OPS CHECK GOOD. NO FURTHER ACTION REQUIRED AT THIS TIME.
ELEVATOR CONTROL/TRIM: DURING FLIGHT THE ELEVATOR TRIM KEPT TRYING TO TRIM NOSE DOWN BUT KEPT SPRINGING BACK, SEE VIDEO. WITH AP DISCONNECTED I TRIED TO MANUALLY TRIM BUT TRIM WAS FROZEN IN PLACE. //SIGNOFF// PERFORMED SUCCESSFUL OPS CHECK OF ELEVATOR TRIM TAB SYSTEM. REF CESSNA 560XLS AMM 27- 32-(13. DETERMINED THE B.£VATOR TRIM ACTUATORS WERE IN NEED OF GREASE. APPLLED MOLYICOTE 33 GREASE (PN: 5565450-28) TO B0111 ACTUATORS.. OPS CHECK GOOD. REF CESSNA 560XLS AMM 12-20-27.
FLOOR EMERG EXIT LIGHT: RIGHT AFT FLOOR EMER LIGHTS INOP. REMOVED AND REPLACED THE AFT EMERGENCY BATTERY PACK IAW CESSNA CE-560XL AMM 33-50-01. OPS CHECK GOOD.
MAIN DOOR: A SEAL UNDER THE BOTTOM STEP ON THE MAIN CABIN DOOR HAS BECOME UNSEATED AND COULD INTERFERE WITH CLOSING THE DOOR. // SIGNOFF// RE-ATTACHED THE SEAL TO THE CABIN ENTRY DOOR FIXED STEPS REF CE560XL AMM 52-10-02 AND SPM 20-40-30
AFT EMERGENCY LIGHT WILL NOT ILLUMINATE USING THE EMERGENCY LIGHTS BATTERY. THEY DO WORK WITH MAIN DC POWER. // SIGNOFF// VERIFIED AFT EXIT SIGNS AT DIVIDER AND OVER LAVATORY DO NOT ILLUMINATE ON EMERGENCY POWER ALONE, ALSO NOTED EXTERIOR OVER-WING LIGHTS DO NOT ILLUMINATE EITHER. REMOVED AFT EMERGENCY BATTERY PN: 9913-1, SN:1558 IAW CESSNA560XL AMM CH: 33-50-01. TESTED BATTERY ON .BENCH REFERENCING CESSNA 560XL WDM CH:33-50-0 L FIGURE 03. WHEN MONITORING OUTPUT PINS 1, 2, & 4 AND SIMULATING LOSS OF POWER, FOUND THAT VOLTAGE WOULD DROP FROM ~9VDC TO ~5VDC IN UNDER 30SECONDS WITH NO LOAD DETERMINED BATTERY TO BE FAULTY. INSTALLED CUSTOMER SUPPLIED REFURBISHED EMERGENCY BATTERY PN:9913-1, SN: 2777 IAW CESSNA 560XL AMM CH: 33-50-01, AND ALLOWED BATTERY TO CHARGE ON GROUND POWER. OPS CHECK: GOOD REFERENCE FAA FORM8130-3, FORM TRACKING NO. 8TDFAOOO'I001001, WORK ORDER8TDFA DURING INSPECTION NOTED AFT R/H SEAT READING LIGHT DID NOT ILLUMINATE WITH SWITCH. FOUND CORROSION ON BULB MOUNTING SOCKET. REMOVED SOCKET ASSEMBLY AND VERIFIED BULB WAS GOOD ON THE BENCH, AND THAT THERE WAS A LACK OF CONTINUITY FROM TH~ CONNECTOR TO THE SOCKET. REMOVED CORROSION, VERIFIED CONTINUITY AND REINSTALLED LIGHT ASSEMBLY AND CONFIRMED PROPER OPERATION FROM SWITCH PANEL. WORK PERFORMED IA W CESSNA560XL AMM CH:33-20-02
CABIN PRESSURIZATION CONTROL: AIRCRAFT OVER PRESSURIZED ON TAKEOFF OUT OF TETERBORO. RAN CHECKLIST ENDED UP HAVING TO DUMP THE CABIN WITH EMER DUMP. RETURNED TO FIELD DID NOT LAND OVERWEIGHT. // SIGNOFF// WHILE STARTING THE APU APU BLEED AIR SWITCH OFF VISUALLY INSPECTED THE VALVES AND NOTICED OUTLFOW· VALVES CLOSING UNCOMMANDED. THIS HAPPENS IN ANY CONFIGURATION. PERFORMED LEAK CHECKS OFF ALL ACCESSIBLE PLUMBING LN THE AREA OF THE OUTFLOW VALVES. PERFORMED LEAK CHECK OF ALL PLUMBING IN THE AREA OF THE OF THE MANUAL TOGGLE SWITCH AND PRESSURIZATION CONTROLLER WITH NO LEAKS FOUND. PLACED AIRCRAFT IN AIR-MODE AND PERFORMED KAPS STATIC SYSTEM TEST AND VERIFIED PROPER OPERATION OF THE AUTOMATIC PRESSURZATION CONTROLLER. AFTER PERFORMING CHECK TWICE WH:ILE LOOKING FOR FAULTS IN THE PRIMARY OUTFLOW VALVE FOUND.THE VALVE WAS NOW OPENING. OPERATED OUTFLOW IN. MANUAL AND AUTO SERVERAL TIMESWITH NO FAULTS FOUND SUSPECT PRIMARY OUTFLOW VALVE IS THE CAUSE OF DISCREPANCY. .ED OVERHAULED PRIMARY OUTFLOW VALVE IAW CE560XL21-30-00 FABRICATED AND INSTALLED NEW SOLENOID TUBE I/A/W CE-560XLS 8PM 20-10-30 PERFORMED OUTFLOW VALVE CONTROL CHAMBER AND MAUNUAL CONTROL VALVE TUBING LEAK CHECK SYSTEM LEAKS CHECK REDUCED TO 500 FPM. REMOVED AND INSPECTED PLUMBING AT BOTH OUTFLOW VALVES AND TEE FITTING TO MAUNUAL VALVE FOUND O RING DISPLACED ON END OF TUBE ALLOWING LEAK AND TUBE TO HAVE SCORED OUTER WALL. RESTED ORING AND REINSTALLED FITTING ON PRIMARY OUTFLOW VALVE . DISCONNECTED TUBE FROMMAUNAUL VALVE TO OUTFLOW VALVES PERFORMED LEAK CHECK OF LINE ONLY. NO LEAKS CONNECTED LINE TO OUTFLOW VALVE TEE AFTER RESEATING OF FITTING AT PRIMMARY VALVE NO MORE LEAKS NOTED IN AFT HALF OF SYSTEM . TESTED FWD HALF FROM PICOLO TUBE TO MAUNUAL VALVE LEAKS AT 500 FPM REMOVED MAUNUAL VALVE ANF TESTED PLUMBING FROM PICOLLO TUBE TO MANUAL VALVE PLUMBING LEAK CHECKS GOOD CHECKED VALVE ON BENCH AND FOUNFD IT LEAKED AT 500 FPM RECEIVED NEW TUBING. FABRICATED AND INSTALL TUBE REPLACING THE SCORED TUBE PREVIOUSLY
BRAKE PRESSURE LIGHT: DURING TAXI OUT BOTH LOW PRESSURE AND ANTISKID LIGHTS ILLUMINATED ALONG WITH MASTER CAUTION. CIRCUIT BREAKERS DID NOT POP. USED EMERGENCY BRAKES TO STOP THE AIRCRAFT DUE TO COMPLETE LOSS OF BRAKE PRESSURE. // SIGNOFF // TROUBLE SHOT AND FOUND BRAKE RELAY TO BE WORKING INTERMITTENTLY REPLACED RELAY PN# MS24166-D2 IAW CE560XL AMM CH 24-50-03 OPERATIONAL CHECK GOOD AT THIS TIME OF INSTALLATION.
RUDDER TRIM TAB IS CRACKED APROX. 1" ON LOWER AFT CORNER. PERFORMED DOUBLER REPAIR TO RUDDER TRIM TAB LOWER TRAILING EDGE. WORK DONE IAW AQRD ERO-935680 REV IR DATED 11/30/2018
MLG BRAKE PRESSURE, BRAKING ON LANDING ROLLOUT IS WEAK AT SLOWING AIRCRAFT. ALSO EXCESSIVE FORCE IS NEEDED WHEN DOING BRAKE ASSISTED TURNS. BLED LT & RT BRAKE ASSEMBLIES IAW MM 32-32-00. TAXI CHKS GOOD AT THIS TIME.
AILERON AFT SECTOR SHAFT ASSEMBLY HAS CORROSION. REMOVED AND REPLACED THE AILERON AFT SECTOR SHAFT IAW MM 27-10-03.
LEFT ELEVATOR HAS A CORRODED TORQUE TUBE. REMOVED AND REPLACED THE TORQUE TUBE IAW SRM 51-40-03, 51-40-06, AND 55-20-01.
AIRCRAFT HAS HAIL DAMAGE. R & R THE LT & RT AILERONS IAW MM 27-10-01 & SRM 51-60-00 & 51-60-01. R & R THE LT & RT ELEVATORS IAW MM 27-31-01 & SRM 51-60-00 & 51-60-02. PARTS REPLACED RT AILERON PN 6624032-3, SN 0000070, ELEVATOR PN 6634200-9 & SN 0000313 & ELEVATOR RT PN 6634200-1 & SN 0000313.
ACOUSTIC SEAL WILL NOT RETRACT WITH APU & OR ENGINES RUNNING. CAN NOT OPEN MAIN CABIN DOOR WITHOUT DIFFICULTY. GAINED ACCESS TO THE ACOUSTIC SEAL DEFLATION VALVE. WHEN MED TRIM PANEL WAS REMOVED FOUND ONE OF THE ACOUSTIC DOOR LINES PINCHED BY THE PRE CATCH ASSEMBLY. RELOCATED ACOUSTIC SEAL AROUND PRECATCH ASSY. OPS CHECK ACOUSTIC SEAL DEFLATION SEVERAL TIMES WITH BOTH APU AND ENGINES. NO DEFECTS NOTED. IAW MM 52-10-04. OPS CHECKED GOOD SEVERAL TIMES IAW MM 52-10-04.
WHILE EXITING THE RUNWAY, THE ANTI-SKID LIGHT CAME ON AND ALL NORMAL BRAKING ABILITY WAS LOST. STOPPED ACFT ON THE TAXIWAY WITH THE EMERGENCY BRAKING SYSTEM. PERFORMED ANTI-SKID OPS CHECK & FOUND RT TRANSDUCER FAULT BIT ON THE CONTROL FAULT BIT INDICATOR, AND INTERMITTENT CONTROL UNIT FAULT BIT INDICATOR. R & R ANTI-SKID CONTROL UNIT. OPS CHECK GOOD.
ON TAXI OUT, OBSERVED POWER BRAKES CIRCUIT BREAKER TRIPPED WITH MASTER CAUTION AND ANTI-SKID INOPERATIVE ANNUNCIATORS ILLUMINATED. RAN ANTI-SKID INOPERATIVE ABNORMAL CHECKLIST AND RETURNED TO RAMP. NO BRAKING AFTER CAUTIOUSLY MOVING FWD AND HAD TO USE EMERGENCY BRAKING SYS TO STOP. THERE WERE NO ANTI-SKID BITE INDICATORS TRIPPED AND NOTHING ABNORMAL NOTED WITH THE BRAKE LINES, BRAKE RESERVOIR, OR AFT J BOX. BLED BRAKES, SERVICED GEAR & BRAKES BOTTLE, CHECKED ALL ANTI-SKID MOTOR WIRES CHECKED OK, CHANGED ANTI-SKID MOTOR IAW AMM 32-42. OPS CHECKED NORMAL.
DURING TAXI OUT THE "ANTISKID INOP" LIGHT ILLUMINATED FOLLOWED SHORTLY THEREAFTER BY THE "PWR BRKS" CIRCUIT BREAKER POPPING. R & R THE HYD PUMP MOTOR IAW MM 32-44-20. OPS & LEAK CHECKED GOOD. TAXI CHECKED GOOD.
DURING TAXI OUT THE "POWER BRAKES" CIRCUIT BREAKER TRIPPED. LOST ALL BRAKING SHORTLY THEREAFTER AND USED THE "EMERGENCY BRAKE" SYS TO STOP THE ACFT. R & R THE POWER BRAKE MOTOR, (PN MP50B-1, SN 3905) PRESSURE SWITCH, (PN GPP1250-73 S/N 0236273) MOTOR TO HYD PUMP COUPLING, (6517108-4 NSN) POWER BRAKE CIRCUIT BREAKER (PN S2899L15.0 ) AND CONTROL RELAY (PN MS24166-D2). OPS & LEAK CHECKS GOOD. REF MM 32-42-04, MM 32-44-20, MM 32-32-42-06, MM 32-44-00 AND MM 32-40-01. SERVICED GEAR AND BRAKE PNEUMATIC BOTTLE IAW MM 12-13-01.
ON TAKEOFF, RUDDER PEDALS VERY STIFF. CONFIRMED YAW DAMPER OFF. RETURNED. RUDDER BIAS CHECKED NORMAL ON TAXI. AFTER LANDING, ON TAXI IN, CHECKED RUDDER STIFFNESS AND FOUND NORMAL AT IDLE POWER BUT RUDDER BECAME PROGRESSIVELY STIFFER AS POWER ADVANCED. COULD NOT DUPLICATE AFTER COMPLETE RUDDER BIAS SYS OPS CHECK, INSTALLED O/H RUDDER BIAS SHUTOFF VALVE. OPS CHECKED GOOD IAW MM 27-20-05.
WHEN APPLYING THE RT BRAKE, THE BRAKE GRABS AND THE ACFT SHUTTERS, MOST NOTICEABLE AT TAXI SPEED.
RUDDER PEDALS HAVE GRINDING FEELING DURING TAKEOFF ROLL AND IN-FLIGHT.
RUDDER PEDALS GRINDING DURING TAKEOFF ROLL AND IN-FLIGHT. GRINDING IS FELT W/POWER ON OR IDLE, & W/ AUTO-PILOT AND YAW DAMP ON OR OFF. GRINDING IS NOT FELT DURING STATIC CHECKS OR LOW SPEED TAXI REGARDLESS OF POWER SETTINGS. FOR BINDING AND DEFECTS. NONE NOTED. REMOVED ACCESS PANELS AND TALE STINGER TO CHECK RUDDER CELL CRACK. CRECES AND SURROUNDING PULLEYS FOR DEFECTS. NONE NOTED. LUBRICATED ALL VISIBLE RUDDER CABLE PULLEYS AND BELL CRANK. EXTRA TIME NEEDED TO REMOVE SCREWS IN ACCESS PANELS THAT WERE HEAVILY PAINTED OVER. CHECKED RUDDER CABLE TENSIONS AND FOUND RUDDER SERVO TENSION LOW. RESET CABLE TENSION TO SPECS AS REQUIRED. RECHECKED RUDDER PANEL. ALL CHECKED GOOD. SAFETIED TURN BARRELS. CHECKED NOSE STEERING CABLES AND RUDDER PEDALS FOR DEFECTS. FOUND STEER ARM AND KNUCKLE WITH ACCESSIVE PLAY. ALSO FOUND NOSE WHEEL OUT OF BALANCE ONCE REMOVED AND CHECKED. REBALANCED NOSE TIRE TO SPECS. OK TO CLOSE ALL TAIL SECTION ACCESS PANELS AND STINGER. OK TO INSTALL NOSE WHEEL. REINSTALLED AFT PANELS. REMOVED AND REPLACED NOSE STEERING ARM AND KNUCKLE. REINSTALLED NOSE WHEEL ASSY. BRGS REPACKED. MAINT PERFORMED IAW MM CHPS 22-11-01 AND 27-20-03. RUDDER STEERING TRAVEL CHECKS DUE. GEAR SWING DUE PERFORMED TRAVEL CHECK ON RUDDER AND FOUND IN NEED OF ADJUSTMENT. TRAVEL AT 27 DEGREE LT AND RT THROW. REMOVED STINGER AND ADJUSTED RUDDER TRAVEL TO 28.5 DEGREE IAW MM CH 27-20-00. REMOVED STEERING ARM SUPPORT BACKED FOR ACCESS. INSTALLED NEW LWR FORK. REINSTALLED STEERING ARM SUPPORT BRACKET. INSTALLED NEW STEERING ARM. WORK PERFORMED IAW MM SECTION 32-50-00. MX NOTE: NOSE WHEEL AND TIRE ASSY. WAS INSTALLED IAW MM SECTION 43-41-01 USING NEW AXLE TUBE AXLE TUBE WAS REPLACED DUE TO EXCESSIVE PITTING AND CORROSION. PERFORMED JACKING AT AFC AND PERFORMED GEAR SWING. OPS CHECK GOOD. PARTS REPLACED: TUBE AXLE PN 0842000-36, FORK LOWER PN 5542304-3, BOLT PN NAS464PSLA28.