N681QS
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
WHEN CLOSING THE MAIN CABIN DOOR FROM EITHER INSIDE OR OUTSIDE, THE DOOR COMES UP NORMALLY BUT THE LOCKING HANDLE DOES NOT MOVE. CLEANED CABIN DOOR LOCKING PINS IAW CABIN DOOR SERVICING IAW AMM 12-20-40.
UPON DEPARTURE FROM PSP FLAPS WERE SELECTED TO THE UP POSITION AS USUAL. FLAPS FAIL AMBER CASS MESSAGE CAME UP INDUCTIONS SHOWED FLAPS WERE STUCK IN THE FLAPS 1 POSITION. POSITION CONFIRMED VISUALLY OUTSIDE. QRH COMPLETED WITH NO SUCCESS. FLAPS CURRENTLY REMAIN IN 1 POSITION. REMOVED FAILED FLAP CONTROLLER P/N:8909324-5 S/N:0166 DUE TO "FLAPS FAIL AMBER CAS MESSAGE" AND INSTALLED A CUSTOMER SUPPLIED REPAIRED FLAP CONTROLLER P/N:8999324-1 S/N:0307. FLAP MOVEMENT CHECK GOOD. OPERATIONAL CHECK GOOD. ALL WORK COMPLIED WITH IN REF TO CE680A AMM 27-50-25.
DURING STARTUP TAXI AND CRUISE FLIGHT, STRONG PRESENCE OF JET EXHAUST THROUGH THE CABIN AND COCKPIT. MORE PRESENT WHEN THE LEFT ENGINE WAS STARTED. REPLACED HEPA FILTER. OPS CHECK GOOD. IAW CE680A AMM 21-60-00
CORROSION UNDER LH LOWER VORTEX GENERATOR TAIL CONE STINGER. RESOLUTION: ACCOMPLISHED MINOR REPAIR IAW RFTS-112233
MAIN ENTRY DOOR APPEARS OVER EXTENDED ONLY SITTING 1-2" OFF THE PAVEMENT AND STEEPER THAN NORMAL. REQUEST IT BE ASSESSED. UPON ARRIVING TO THE AIRCRAFT WE NOTICED THE AIRCRAFT WAS PARKED ON A NON LEVEL SURFACE OF THE RAMP. MOVED AIRCRAFT INTO THE HANGAR ONTO A LEVEL SURFACE AND FOUND NO DEFECTS WITH THE MAIN ENTRY DOOR HEIGHT. ADVISED MCC OF FINDINGS, OK TO SIGN OFF. WORK DONE IAW AMM 52-10-00.
LAV FLOOR EMERGENCY LIGHT INOP GAINED ACCESS TO AIRCRAFT. APPLIED ELECTRICAL POWER AND TURNED ON EMERGENCY LIGHTS, VERIFIED THAT LAV FLOOR LIGHT IS NOT ON. TURNED OFF ELECTRICAL POWER, AND EMERGENCY LIGHTS. REMOVED LAV EMERG LIGHT PANEL, PERFORMED GVI ON PANEL AND WIRING. NO DEFECTS NOTED. VERIFIED THAT CONNECTED FOR LAV FLOOR EMERGENCY LIGHT IS SECURED. FOUND CONNECTOR NOT SECURED, SECURED CONNECTOR AND INSTALLED PANEL. APPLIED BATTERY POWER AND EXTERNAL POWER AND VERIFIED THAT LAV FLOOR LIGHT COMES ON WITH EMERGENCY LIGHT SWITCH. WORK COMPLETED IAW MM 33-50-00.
FLOOR EMERG EXIT LIGHT: FLOOR PATH EMERG LIGHTS AT SEAT 5 AND 8 DO NOT ILLUMINATE UNTIL POWER IS APPLIED TO THE AIRCRAFT. THE LAV FLOOR PATH LIGHTING DOES NOT ILLUMINATE AT ALL.(PRE FLIGHT) //SIGNOFF// REMOVED #4 FAULTY EMER BATTERY PACK CBS28-1 SN007152 AND INSTALLED REPAIRED CUSTOMER SUPPLIED EMER BATTERY PACK F PN;CBS28·1 SN:4621M, WORK DONE IN REFERENCE TO CESSNA MODEL 680A AMM 33-50-00 REMOVED 114 FAULTY EMER BATTERY PACK PN:CBS28·1 SN:2111M AND INSTALLED REPAIRED CUSTOMER SUPPLIED EMER BATTERY PACK F PN;CBS28·1 SN:008954, WORK DONE IN REFERENCE 'TO CESSNA MODEL (I80A AMM 33-50-00 ·POWER UP AIRCRAFT AND ARM THE BATTERIES FOR 90 MINUTES TO GUARANTEE A FULL CHARGE ON THE BATTERIES, PERFORME:P OPS CHECK OF 'THE EMERGENCY LIGHTING SYSTEM. OPS CHECK GOOD. CLOSED UP ALL GALNED ACCESS, WORK DON IN REFERENCE TO CESSNA MODEL 680A AMM 33-50-00
DURING INITIAL CABIN PREFLIGHT INSPECTION FOUND EXIT SIGN ON WALL BEHIND SEAT SEVEN TO BE INOP. ALSO, THE EXIT SIGN BELOW THE LAV IS INOP. ALL OTHER EMERGENCY LIGHTING WORKS CORRECTLY. COMPLIED WITH TC NO TC-FLT-33-1001 EMERGENCY LIGHTING POWER SUPPLY BATTERY EXERCISE PROCEDURE. NO DEFECTS NOTED AT THIS TIME. REV 2 DATE 200CT2022.
CABIN EMERG LIGHT: ALL CABIN EMERGENCY LIGHTS ARE INOP. POWERED UP AIRCRAFT AND VERIFIED ALL CABIN EMERGENCY LIGHTS WERE !NOP. REMOVED LH CABIN LOWER ACCESS PANEL AND VERIFIED EMERGENCY LIGHTING INERTIA SWITCHES IN THE CABIN AND COCKPIT WERE NOT TRIGGERED. RE INSTALLED CABIN LOWER ACCESS PANEL TO NORMAL CONFIGURATION, CONNECTED GPU AND LETTING BATTERY CHARGE FOR SOME TIME. PERFORMING OPERATIONAL CHECK OF EMERGENCY LIGHTING SYSTEM ONCE FULLY CHARGED. ONCE CABIN EMERGENCY LIGHTS WERE FULLY CHARGED. PERFORMED OPERATIONAL CHECK, OPERATIONAL CHECK GOOD. ALL WORK PERFORMED !AW CESSNA MODEL 680A MAINTENANCE MANUAL 33·50·00.
GSD FAIL 3 AMBER CAS: GSD FAIL 3 IN CRUISE FLIGHT, RAN THE QRH. HAD TO BLOW THE GEAR BOTTLE AFTER GEAR WAS DOWN BECAUSE OF NO INDICATION FROM THE FAILURE. TROUBLESHOT STALL FAIL CAS MESSAGE TO A BAD G-SWITCH. REMOVED BAD SWITCH AND INSTALLED INSTALLED A REPAIRED STALL PROTECTION COMPUTER. OP'S CHECK GOOD ALL WORK DONE IAW CL650 27-35-19.
2-EACH RIGHT WING FUEL TANK FUEL CHECK VALVE DETACHED FROM MOUNT.
ACCOMPLISHED TEMPORARY REPAIR AND PROTECTION OF THE LH ENGINE AGB AFT COVER AND FLANGES. IAW PRATT & WHITNEY CANADA MM 72-60-01. REPEAT STEPS (1) THRU (4) AT EVERY AIRCRAFT MINOR INSPECTION (1A, 800 HR.) UNTIL PERMANENT REPAIR ACCOMPLISHED.
ACCOMPLISHED TEMPORARY REPAIR AND PROTECTION OF THE RH ENGINE AGB AFT COVER AND FLANGES. IAW PRATT & WHITNEY CANADA MM 72-60-01. REPEAT STEPS (1) THRU (4) AT EVERY AIRCRAFT MINOR INSPECTION (1A, 800 HR.) UNTIL PERMANENT REPAIR ACCOMPLISHED.
CABIN EMERGENCY LIGHT: WITH POWER OFF, EMERGENCY LIGHTS OFF AND BATTERIES DISCONNECTED, THE LIGHT UNDER SEAT 5 & 8, THE LIGHT OVER SEAT 7, THE LEFT OVER WING LIGHT PLUS THE EXIT LIGHT OVER THE LAV STAY ON. REMOVED AND INSTALLED REPAIRED EMERGENCY LIGHTING BATTERY PACKS IN THE NR 2 AND NR 3 POSITIONS. OPERATIONAL CHECKED GOOD IAW CE-680A MM 33-50-06.
RIGHT MLG GREEN DOWN & LOCKED LIGHT INTERMITTENT. RAN CHECKLISTS, GEAR WAS BLOWN DOWN HAD 3 GREEN LIGHTS ON LANDING.
IN STRAIGHT & LEVEL FLIGHT RUDDER TRIM REQUIRES 1/2 DEFLECTION TRIM TO LT. WITH FLAPS 35 & APPROACH AIRSPEED 3/4 DEFLECTION TO LT IS REQUIRED.
IN STRAIGHT & LEVEL FLIGHT RUDDER TRIM REQUIRES 1/2 DEFLECTION TRIM TO LT. WITH FLAPS 35 & APPROACH AIRSPEED 3/4 DEFLECTION TO LT IS REQUIRED, REMOVED THE STINGER & INSTALLED BOTH THE RUDDER PEDAL BLOCKS & THE AFT SECTOR RIG PIN, WITH BOTH INSTALLED THE RUDDER IS FAIRED. NEED TO CHECK TENSIONS & RIG SYS TO NEUTRAL. CHECKED RUDDER CABLE TENSIONS, FOUND LOWER TENSIONS 10 LBS LOW. ADJUSTED TENSIONS IAW MM 27-20-00. OPERATIONS CHECKED GOOD. OK TO CLOSE ACCESS, PERFORMED TRAVEL CHECKS. TRAVEL CHECKS GOOD IAW MM 27-20-00. CONFIRMED RUDDER TRAVEL CHECKS GOOD. COMPLIED WITH TRAVEL CHECKS ON BOTH FLAPS. IAW MM 27-51-00 OPERATIONS & TRAVELS CHECKED GOOD.
TRIED TO MOVE THE RUDDER TRIM BOTH LT & RT. THE RUDDER TRIM WOULD NOT MOVE EITHER WAY. ON TAXI IN AFTER LANDING THE RUDDER PEDALS WERE STIFF TO STEER THE AIRPLANE. NO MECHANICAL DEFECTS WERE NOTED, HOWEVER THE RUDDER TRIM ACTUATOR DID NOT APPEAR TO HAVE MUCH GREASE IN IT. DUE TO BACKORDER ON THE RUDDER TRIM ACTUATOR THE RUDDER TRIM ACTUATOR WAS LUBED IAW AMM 12 21-01. NO BINDING OR STIFFNESS WAS NOTED DURING GND OPERATION. VISUALLY INSPECTED RUDDER & RUDDER COMPONENTS, CABLES, RUDDER TRIM CABLES, RUDDER BIAS ACTUATOR, BLANKET & BLEED PORTS, NO DEFECTS NOTED. VISUALLY INSPECTED THE NWS TO INCLUDE PROPER MOVEMENT IAW THE MM, SLUGGISH MOVEMENT, PERFORMED LOW SPEED TAXI CHECK, NO DEFECTS NOTED. PERFORMED LOW SPEED TAXI CHECK, OPERATIONS ARE SATISFACTORY. ACCOMPLISHED TASK TC-5XL 53-110306 FUSELAGE BILGE DRAIN CLEANING. VISUALLY INSPECTED, NO DRAINS WERE FOUND TO BE BLOCKED, RAN WATER THROUGH MOISTURE DRAINS, NO CLOGGING NOTED. LUBED THE RUDDER TRIM ACTUATOR & NOTED THE PERFORMANCE OF MOVEMENT. RUDDER TRIM ACTUATOR HAS BEEN LUBED WITH DC 33 AS REQUESTED. THE TRIM ACTUATOR MOVEMENT IS SMOOTH AT THIS TIME.
EXIT LIGHT OVER MAIN ENTRY DOOR WAS SEEN TO FLICKER ON AND OFF WHILE DECENDING FOR APPROACH. F/O NOTED A WISP OF SMOKE COMING FROM LIGHT. AFTER UNEVENTFUL LANDING AND DEPLANEING OF PASSENGERS, INSPECTED LIGHT AND FOUND ALL BULBS WERE OUT.
RUDDER AUTO/PILOT SERVO CABLE BRACKET IS CRACKED. R & R RUDDER AUTO/PILOT SERVO CABLE BRACKET IAW SRM 51-40-03.
RT WING TO FUSELAGE FAIRING ANGLE SUPPORT CRACKED IN SEVERAL SPOTS. R & R RT AFT STRAP (PN 6610146-20-1) IAW SRM 51-40-03.
5 MINUTES AFTER ENGINE START, GRAY SMOKE BEGAN FILLING CABIN. APU HAD BEEN RUNNING FLAWLESSLY FOR 40 MINUTES. PERFORMED VISUAL INSP OF THE APU INLET, FOUND OIL RESIDUE IN THE APU INTAKE. REMOVE EXCHANGE NOZZLE, INLET AIR DUCT, CONNECTORS, FUEL AND DRAIN LINES AND STARTER/GEN WIRES FROM APU. REMOVED STARTER/GEN. REMOVED APU FROM ACFT. SWAPPED COMPONENTS FROM OLD APU OVER TO NEW APU. INSTALLED APU BACK IN ACFT. PERFORMED APU OPS TEST. WORK DONE IAW THE MM 49-10-00. INSTALLED NEW APU. LEAK AND OPS GOOD.
VIBRATION IN AIRFRAME. MOST NOTABLE AT HIGHER SPEEDS-290K. NOT NOTICEABLE AT SPEEDS LESS THAN 240K. NO CHANGES WITH CONFIGURATION CHANGE. VIBRATION FELT THROUGHOUT AIRFRAME, AUTOPILOT ON AND OFF. R & R ELEVATOR, LT TRIM TAB HORN BEARINGS AND REPLACED RUDDER TRIM TAB HORN BEARINGS IAW MM 20-10-08.
DURING FTL LT PFD AND MFD DISPLAYED ATTITUDE AND HEADING FAILED. TROUBLESHOT AND FOUND NR 1 AHRS TO BE INOPERATIVE. R & R NR1 AHRS UNIT REPAIRED IAW MM 34-21-01. OPS CHECKED GOOD.
AT 400FT AND SELECTING FLAPS FROM 15 TO ZERO DEGREES, FLAPS INDICATOR STOPPED AT 7 DEGREES.
AT 400 FT AND SELECTING FLAPS FROM 15 TO ZERO DEGREES, HYD PRESS ANNUNCIATOR AND MASTER CAUTION BEGAN FLASHING AND FLAPS INDICATOR STOPPED AT 7 DEGREES. IAW AA2 CB WAS PULLED AND LIGHTS EXTINGUISHED. RESET CB FOR LDG AND LT FLAPS A 7 DEGREES FOR LDG AND POST FLT. REMOVED RT FLAP ACTUATOR DUE TO FAILURE AND INSTALLED NEW ACTUATOR IAW MM 27-51-00. OPS, LEAK, AND TRAVEL CHECKS GOOD.
AFTER TAKEOFF, FLAPS STOCK AT 7 (DEG) WITH ACCOMPANYING MASTER CAUTION AND HYD PRESS ANNUNCIATIONS. CAUTION CEASED WHEN FLAPS SELECTED 15 (DEG) AND GEAR DOWN. VERIFIED DISCREPANCY TROUBLESHOT TO FAULTY LT FLAP ACTUATOR. GAINED ACCESS TO LT FLAP ACTUATOR AND REMOVED FROM ACFT. INSTALLED NEW LT FLAP ACTUATOR AND RIGGED FLAPS. PERFORMED TRAVEL AND OPS CHECKS OF FLAP SYS. TRAVEL AND OPS CHECK GOOD. RESECURED HARDWARE WITH COTTER PINS AND SEALED FASTENERS. PERFORMED LEAK CHECK. LEAK CHECK GOOD. SERVICED HYD SYS. ALL WORK IAW MM CH 27-50-00.
FLAP OVERSPEED ON DEPARTURE CLIMB. COMPLIED WITH FLAP OVERSPEED INSPECTION IAW MM 5-50-00 NO DEFECTS NOTED.
PIC SIDE WINDSHIELD SHATTERED AT FL430. REMOVED AND INSTALLED A NEW WINDSHIELD IN THE PILOTS POSITION. INSTALLED WITH NEW HARDWARE- TORQUED PER M/M. INSTALLED WITH NEW STICK N STRIP SEAL. PRESSURIZED AIRCRAFT. LEAK RATE WITHIN LIMITS. RAN A/C TO OPS CHECK PILOT'S HEATED WINDSHIELD- OPS CHECKED GOOD- PERFORMED IAW CE560XL M/M CH 56-11-00/30-41-00/71-00-00.
DURING TAKEOFF ROLL, ABORTED TAKEOFF (BELOW 70KTS) DUE TO ILLUMINATION OF NO TAKEOFF ANNUNCIATOR AND NO TAKEOFF HORN. TROUBLESHOT SYSTEMS. FOUND EXCESSIVE MOISTURE AND CORROSION IN THE LT SPEEDBRAKE DISCONNECT PLUG PL001. REPLACED PINS, SOCKETS AND PLUG BACKSHELLS WITH NEW IAW CE WDM CH 20-10-04. PERFORMED OPS CK OF "NO TAKEOFF" SYSTEM. OPS CK GOOD.
ON TAKEOFF WHEN GEAR WAS RETRACTED GEAR UNLOCK LIGHT & HYD PUMP ANNUNCIATOR LIGHT REMAINED ILLUMINATED. GEAR WAS CYCLED DOWN WITH LOCK INDICATION HYD PUMP EXTINGUISHED. ITEM IS UNDER INVESTIGATION.
AFTER TAKEOFF FROM LNK, NOTICE BURNING ODOR IN COCKPIT WITH POWER AT OR ABOVE 70 PERCENT AND APU OFF, ACCOMPLISHED AIR TURNBACK TO LNK. INVESTIGATED AND FOUND WATER SOCK AREA CLEAN AND FREE OF ODOR PER CESSNA 560XL MM CHAPTER 21-50-00, SYSTEM OPS CHECKED OK. RAN AIRCRAFT ON GROUND AT DIFFERENT POWER SETTING AND COULD NOT DUPLICATE STRONG ACID ODOR.
AFTER TAKE OFF AN ACRID SMELL WAS DETECTED IN COCKPIT. THIS WAS FOLLOWED BY A BURNING IN THE THROATS AND EYES OF PASSENGERS AND CREW. DECLARED AN EMERGENCY, O2 GEAR WAS DONNED AND RETURNED TO KLNK. NO SMOKE WAS EVER VISIBLE. TROUBLESHOT TO FIND SOURCE FOR ODOR, BORESCOPED #1 AND #2 ENGINE BLEED PORTS AND FOUND NO TRACES OF OIL OR RESIDUE. INSPECTED COELESCER SOCK FOUND NO ODOR OR RESIDUE, REMOVED AND REPLACED ACM, PERFORMED ENGINE RUN UP AT ALL POWER SETTINGS , NO SIGN OF ANY ODORS, SYSTEM LEAK AND OPS CHECK GOOD IAW CESSNA 560XL MM TASK 21-51-00 , 12-19-02-161.