N694QS
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
RH ENGINE HAS EVIDENCE OF AXIAL CRACKING ON HPT STAGE 1 BLADES (4 TOTAL BLADES).
MAIN CABIN DOOR DIFFICULT TO CLOSE FROM INSIDE. FEELS LIKE PIN ALLIGNMENT, TOP AFT PIN. FUNCTIONAL FROM EXTERIOR. DOOR IS ALSO INTERMITTENTLY SLOW TO OPEN. UPON INSPECTING OF THE MED. FOUND UPPER AFT CABIN DOOR STOP LOOSE. ADJUSTED THE CLEARANCE BETWEEN THE CABIN DOOR STOP AND THE CABIN DOOR. VERIFIED THE MED IN THE FULL CLOSED AND LATCHED POSITION BETWEEN THE CABIN DOOR STOP AND THE CABIN DOOR. PREFORMED OPERATIONAL CHECK OF THE MED. OPS CHECKS GOOD. NO DEFECTS NOTED. IN REF. WITH CE-680A MM 52-10-00.
EMERGENCY LIGHTING: EMERGENCY LIGHTS DO NOT ILLUMINATE IN THE ARM POSITION. CORRECTIVE ACTION; REPLACED THE EMERGENCY LIGHT BATTERY PACK ASSEMBLY BATTERY !AW SIL÷CBS28+2024-001. OPS CHECK GOOD.
FOUND LAVATORY DECK CORRODED ON UNDER SIDE. COMPLIED WITH RFTS-113043 N694QS (680A-0226) TOILET SEAL PANEL CORROSION REV.0 DATED 21FEB25.
AFT FUSELAGE FAIRING SUPPORT CORROSION
CABIN EMERG LIGHT: DURING THE POWER ON CHECKLIST, WITH THE BATTERIES OFF, WHEN THE EMER LTS SWITCH IS PLACED IN THE ARM POSITION NONE OF THE INTERIOR EMERGENCY LIGHTS ILLUMINATE. RAN THE QRH FOR EMERGENCY LIGHTS FAIL PERFLIGHT TEST AND TRIED CHARGING THE EMERGENCY BATTERIES. THEY STILL WOULD NIT ILLIMUNIATE IN THE ARM POSITION WITH THE BATTERIES OFF. THE BATTERIES WERE CONNECTED PRIOR TO CONDUCTING CHECKS. CORRECTIVE ACTION: PERFORMED OPS CHECK. ALL CHECKS SATISFACTORY. NO DEFECTS NOTED. IAW TC-FLT-33-1001 AND CESSNA 680A AMM 33-50-00
DURING THE EMER LIGHT TEST WHILE SELECTING TO ARM THE EMERGENCY EXIT AND OVERHEAD LIGHTS DID NOT ILLUMINATE. WHEN SELECTING EMER LIGHT TO ON THE LIGHTS WOULD ELIMINATE CORRECTLY. WE THEN CHARGED THE BATTERIES FOR 30 MINUTES WITH THE APU. ON THE SECOND TEST THE LIGHTS CAME ON FOR TWO SECONDS BEFORE GOING OUT. AFTER THE SECOND CHARGING AND TEST, THEY CAME ON FOR APPROXIMATELY EIGHT SECONDS. CORRECTIVE ACTION: PERFORMED GVI OF ALL 4 BATTERY PACKS AND G SWITCHES WITH NO DEFECTS NOTED. IAW CE-680A MM 33-50-00
RUDDER: DURING APPROACH WITH 15 KTS LEFT CROSSWIND THE RUDDER PEDAL SEEM TO BE BINDING AND HARD TO PUSH FOR CROSSWIND ALIGNMENT. THE YAW DAMPER WAS VERIFIED OFF. AND THERE WERE NO CAS MESSAGE. BUT FELT LIKE RUDDER WAS BEING LIMITED. SEEMS TO FUNCTION FINE ON GROUND WHILE TAXING. CORRECTIVE ACTION; COMPLETED GVI ON RUDDER, TAXI CHECK RUDDER PADDLES OPERATION, RUDDER BAIS SYSTEM OPS CHECK. NO FAULTS FOUND. CANNOT DUPLICATE SQUAWK. RUDDER SYSTEM OPS CHECKED GOOD. REF: CE-680A AMM 27-20-00.
HALF WAY DURING FLIGHT AT 40,000 THE RIGHT WINDSHEILD HEAT INOP CAS MESSAGE CAME ON. PROCEDURE ON CHECKLIST WAS COMPLETED. THIS IS A REPEAT WRITE UP. REMOVED FAILED AC GEN PN: 9914443-1 SN: 537. INSTALLED NEW CUSTOMER SUPPLIED AC GEN PN: 991443-1 SN: 1203 AS REQUIRED. OPERATIONAL CHECKS GOOD. WORK DONE IAW AMM 24-20-05
LAV EMERG LIGHT: WITH THE EMER LIGHT TO ARM AND THE MAIN BATTERIES OFF, THE EXIT SIGN ON THE BULKHEAD BEHIND SEAT 7 IS INOP, THE SPOT LIGHT AT SEAT 7 IS INOP, THE KICK PLATE LIGHT UNDER THE LAV IS INOP, AND THE SPOTLIGHT AT THE LAV IS INOP. ///SIGN-OFF/// COMPLIED WITH TASK CARD TC-FLT-33-1001 BY ALLOWING THE EMERGENCY LIGHT BATTERIES TO CHARGE FOR 60 MINUTES. PERFORMED DISCHARGE OF THE EMERGENCY LIGHT POWER SUPPLY BATTERIES, ALL LIGHTS REMAIN ILLUMINATED LONGER THAN 10 MINUTES. PER TASK CARD THE BATTERIES ARE AIRWORTHY. RE- CHARGED FOR 60 MINUTES, CALLED MCC OF FINDING AND THEY ELECT TO SIGN OFF. ALL WORK WAS DONE AS PER CE-680A AMM 33-50-00.
CABIN DOOR OPEN AMBER CAS: CHECK DOORS AMBER CAS AND AMBER DOOR OPEN LIGHT ON THE HANDLE ALL ILLUMINATED WITH THE DOOR CLOSED. QRH COMPLIED WITH. RESULTS WERE UNSUCCESSFUL. VERIFIED THAT THE EXTERNAL CABIN DOOR OPEN LIGHT AND THAT THE CABIN DOOR OPEN CAS MESSAGE WAS ILLUMINATED. COMPLIED WITH THE CABIN DOOR OPEN RESET PROCEDURE I.A.W. AFM 3-510-28 CONFIGURATION AA FAA APPROVED 68AFM-02. 2. COMPLETED 5EA OPEN/CLOSE OF MAIN ENTRY DOOR, OPS CHECKS OF MAIN ENTRY DOOR AND DOOR CAS/SECURITY LIGHTS AND SYSTEM GOOD, NO DEFECTS NOTED.
IMPACT DAMAGE - L/H WING, UPPER AND LOWER SKINS, TRAILING EDGE, CWS 320 - WS 369. REFERENCE FR-680A-0226-10757 AND FAA FORM 8100-9 DATED 06JUL2022. REFERENCE TEXTRON AVIATION LETTER DQ34743M1, 680A-0226 (N694QS)LEFT WING LOWER SKIN DIS-BOND (FR-680A-0226-10757) DATED 18AUG2022.
GSD FAIL 2 AMBER CAS: SHORTLY AFTER BEGINNING OUR DISSENT FROM FLIGHT LEVEL 410 THE GSD FAIL 2 AMBER ICAS MESSAGE ELIMINATED. THE AMBER MESSAGE CHECKLIST DROVE US TO BLOW THE GEAR DOWN. STOWED LANDING GEAR HANDLE AND SAFETED. SERVICED LANDING GEAR BOTTLE WITH NITROGEN. OPENED PANEL 316AR. RESET PNEUMATIC OVERRIDE VALVE ON LANDING GEAR CONTROL MANIFOLD. CLOSED PANEL 316AR IAW CE-680A AMM 2-10-45 (09-15 SL). JACKED AIRCRAFT MADE SURE LANDING GEAR SHUTTLE VALVE WERE BACK IN THE CORRECT POSTIONS PERFORMED GEAR SWINGS AND BLED HYDRALIC SYSTEM RESERVICED HYDRAULIC SYSTEM UNJACKED AIRCRART CLOSED ACCESS GEAR SWINGS AND CLOSED ACCESS. GEAR SWINGS AND HYDRAULICS OPERATIONAL CHECKS SATISFACTORY IAW CE-680A AMM 12-10-45 AND CE-680A AMM 32-30-00 SENT ARES DOWNLOADS TO TEXTRON (0914SL). REMOVED AND REPLACED GSD 2DATA CONCENTRATOR UNIT (DCU) WITH A REPAIRED DCU, IAW CE·680A AMM 31-40-10 AND LOADED SOFTWARE IAW CE-680A AMM 42-10-15. SOFTWARE LOADING AND OPERATIONAL CHECKS WERE SATISFACTORY. PN OFF 011-01457-01, SN OFF 2JH007258, PN ON 011-01457-01 SN ON 2JH005444.
CHAFE IN LOWER FUSELAGE SKIN CAUSED BY ANTI-ICE CROSSFLOW VALVE. ACCOMPLISHED TEXTRON STANDARD REPAIR SR-680A-ATA53-22175 DATED 7/19/2019, STEPS 1-5, STEPS 6-8 N/A DUE TO COMPLETION OF SB680A-30-01. INCLUDED FAA FORM 8100-9 DATED 7/19/2019.
WHILE CLOSING THE MED THE DOOR SUPPORT ROD WAS BENT. THIS ALSO PUT ABOUT A 1/2" CRACK IN THE INNER LINER OF THE MED. "CORRECTIVE ACTION" INSTALLED NEW LIFT LINK ASSEMBLY P/N 7411323-2 NSN AS REQUIRED. RIGGED THE DOOR AS REQUIRED.
GEAR POSITION & WARNING: LANDING GEAR EXCEEDED GEAR EXTENSION SPEED AT APPROX 230KTS CORRECTIVE ACTION JACKED AIRCRAFT, PERFORMED SLOW CYCLE OF LANDING GEAR. INSPECTED LANDING GEAR, ATTACH STRUCTURE, HEAR DOORS AND LANDING GEAR CLEARANCE CHECKS. DOWN JACKED ALL CHECKS GOOD. WORK DONE IAW CESSNA 680A MM 5-50-00.
WE ARE FINDING MORE OF THESE PIVOT FITTING ASSEMBLY HAVING CRACKS PN 6631102-15 & T CLIP PN 6631202-7 HAVING LOOSE HARDWARE.
HORIZONTAL STABILIZER FITTING ASSY CRACKED ABOVE CLIP ATTACH POINT.
BRAKE FAILURE AFTER LANDING WHILE TAXIING TO THE FBO. STOPPED ACFT USING EMERGENCY BRAKES. PERFORMED SATISFACTORY RINGOUT OF HIGH PRESSURE SWITCH FOR ANTI-SKID CONTROL MOTOR PUMP WITH PRESSURE AND WITHOUT PRESSURE ON THE SYSTEM. VERIFIED BRAKE CONTROL MOTOR RELAY KN003 WAS STAYING LATCHED AND PROVIDING POWER TO SKID CONTROL MOTOR PUMP AT ALL TIMES. PERFORMED SATISFACTORY RINGOUT OF DIODES DN004 AND DN003 AT BRAKE CONTROL MOTOR RELAY KN003. BRAKE CONTROL MOTOR RELAY KN003 HAS BEEN VERIFIED AS DEFECTIVE. REMOVED RELAY KN003 (PIN: MS24166·D2, SN: NSN) AND INSTALLED NEW KN003 (PIN: MS24166·D2, S/N: NSN, 8130-3 APPROVAL NO.: ODA·100129-CE) LAW MODEL MM3242-08 AND 20-20·00. RINGOUT PROCEDURE PERFORMED LAW MM 3240-0T PERFORMED SATISFACTORY OPS CHECK OF ANTI-SKID CONTROL IAW MM 3242-00.
ON ROLLOUT ANTI-SKIP INOPERATIVE LIGHT ILLUMINATED. DURING TAXI IN LOW BRAKE PRESSURE LIGHT ILLUMINATED. FOLLOWED BY LOSS OF BRAKES. USED EMERGENCY BRAKING TO STOP ACFT. CIRCUIT BREAKER DID NOT TRIP. NO BREAK FLUID LEAKING NOTICED. REMOVED SUSPECTED FAULTY BRAKE HYD POWERPACK, INSTALLED NEW BRAKE HYD POWERPACK. PERFORMED BRAKE BLEEDING AND OPS TEST, NO DEFECTS NOTED AT THIS TIME. SERVICED BRAKE RESERVOIR TO FULL WITH HYDRAULIC FLUID. REF MM 32-42-06 AND 32-42-00.
CORROSION FOUND ON RT LANDING GEAR RETRACT ACTUATOR TRUNNION ATTACH POINT. INSTALLED RT MLG TRUNNION ASSY REF MM 32-10-00.
COPILOTS PFD FAILED RED X THEN BLANK SCREEN-- IT RETURNED TO OPERATING STATUS AFTER A FEW MINUTES- ALSO A VERY STRONG ELECTRICAL BURNING ODOR WAS PRESENT IN THE COCKPIT AREA. NO CURCUIT BREAKERS WERE POPPED. INSPECTED AND FOUND A STRONG ELECTRICAL ODOR COMING FROM THE BACK OF THE PFD. NO SMOKE WAS NOTED. REMOVED PFD AND REPLACED IT WITH A REPAIRED UNIT. OPS CHECKED GOOD. WORK PERFORMED IN REF TO THE MM 34-25-01.
DOOR SEAL LIGHT ANNUNCIATOR CAME ON IN FLIGHT. DOOR SEAL INOP. PURGED DOOR SEAL WITH NITROGEN. PERFORMED CABIN ENTRY DOOR PRIMARY SEAL TEST IAW MM 52-10-04. OPS CHECK GOOD.
APU FAILED WHILE RUNNING ON THE RAMP, APU FAIL LIGHT ON. APU INOP. COCKPIT FILLED WITH SMOKE, SHUTDOWN APU, STARTED ENGINES, SMOKE CLEARED. REMOVED FAILED APU AND INSTALLED A REPAIRED APU IAW MM 49-10-00. OPS CHECK GOOD. LEAK CHECK GOOD.
AFTER TAKEOFF UPON GEAR RETRACTION THE NOSE GEAR (GREEN) DOWN LOCK LIGHT REMAINED ILLUMINATED. REMOVED DAMAGED NLG CENTERING BUNGEE FROM NLG AND INSTALLED NEW GEAR ASSY REF CMM 32-20-01. REMOVED NLG ACTUATOR AND INSTALLED INPSECTED NLG ACTUATOR IAW AMM 32-30-03 INSTALLED NEW CENTERING BUNGEE. PERFORMED NLG EXTENTION REFECTION TEST IAW AMM 32-30-03.
(PWR BRAKES) CIRCUIT BREAKER POPPED RESULTING IN LOSS OF BRAKE PRESSURE. REPLACED HYD BRAKES POWER PACK AND HIGH PRESSURE SWITCH, BLED BRAKES OPPS CHECKED SATISFACTORY. ALL WORK IAW MM 32-42-00.
FLAPS WILL NOT RETRACT BEYOND 7 DEG WITH THE FLAP HANDLE IN THE 0 POSITION. RECEIVED ACFT WITH FLAPS STUCK HARD AT 15 DEGREES. ATTACHED HYDS AT EXTEND AND RETRACT LINES OFF OF FLAP CONTROL VALVE. FLAPS WOULD NOT EXTEND OR RETRACT WITH APPLIED HYD PRESSURE. MEASURED ACTUATOR ROD LENGTHS WITH HYD PRESSURE APPLIED, THE RT ACTUATOR WOULD MOVE 1/4 INCH WHILE THE LT ACTUATOR REMAINED LOCKED. REMOVED LT FLAP ACTUATOR AND INSTALLED CUSTOMER SUPPLIED P/N 9912007-2 S/N 2568. WORK WAS PERFORMED IAW MM 27-51-04.
FLAPS WILL NOT RETRACT BEYOND 7 DEG WITH THE FLAP HANDLE IN THE 0 POSITION.
DURING A PHASE 5 INSPECTION, FOUND LT WHEEL WELL AFT SPAR CLOSE OUT PANEL CRACKED. (3) CRACKS WERE FOUND BEGINING FROM THE LOWER SKIN ATTACH FLANGE AND GOES STRAIGHT UP THE PANEL. AN SCR HAS BEEN SUBMITTED TO MFG AIRCRAFT UNDER NR 303303.
DURING A PHASE 5 INSPECTION, FOUND LT WHEEL WELL AFT SPAR CLOSE OUT PANEL CRACKED. (3) CRACKS WERE FOUND BEGINNING FROM THE LOWER SKIN ATTACH FLANGE AND GOES STRAIGHT UP THE PANEL. AN SDR HAS BEEN SUBMITTED TO AIRCRAFT UNDER NR 303303.
GEAR 'UNLOCK' LIGHT ILLUMINATED AFTER GEAR RETRACTION. CYCLED GEAR TWICE WITH SAME RESULT. HYD SYSTEM REMAINED PRESSURIZED UNTIL GEAR SELECTED DOWN. ADJUSTED & CHECKED FREE FALL CABLE IAW CESSNA 560XL M/M CHPT 32-30-08
WITH GEAR SELECTED DOWN AND LOCKED (3 GREEN, NO RED) SELECTED FLAP SWITCH TO 15 AND 'HYD' PRESSURE LIGHT CAME ON FLASING WITH MASTER CAUTION FLASHING INSTANTLY WITH NO DELAY.TROUBLESHOT TO FAULTY ANNUNCIATOR PANEL. REPLACED WITH SERVICEABLE UNIT. OPERATIONAL CHECK NORMAL IAW CESSNA 560XL MM 31-50-01.
GEAR UNLOCKED LIGHT REMAINS ON AFTER GEAR RETRACTION. CYCLED BREAKER NO CHANGE. RETURN TO FIELD. JACKED AIRCRAFT & SWUNG GEAR SEVERAL TIMES & COULD NOT DUPLICATE SQK. REPLACED NOSE GEAR UPLOCK SWITCH WITH NEW UNIT IAW CE560XL M/M CHAP 32-61-00. GEAR SWING & OPS CHECK GOOD AT THIS TIME.
AFTER TAKEOFF WITH GEAR SELECTED UP AND FLAPS SELECTED UP MASTER CAUTION ILLUMINATED. (HYD PRESS) (STAB MISCOPARE) AND GEAR (UNLOCK) LIGHTS ILLUMINATED. PLACED GEAR DOWN - ALL LIGHTS WENT OUT-GEAR INDICATED 3 GREEN. PLACED GEAR UP, UNLOCK LIGHT REMAINED ON AND (HYD PRESS) ANNUNCIATION. SWUNG GEAR MULTIPLE TIMES WITH NO FAULTS NOTED. ALL WORK DONE IAW MM CHAP 32-30-05. OPS CHECK AND LEAK CHECK GOOD AT THIS TIME.
ENVIRONMENTAL ODOR DETECTED AFTER APU SHUTDOWN IN FLIGHT. O2 USED FOR DURATION OF FLIGHT. NO VISIBLE SMOKE NOTED. ITEM IS UNDER INVESTIGATION.
DURING PHASE 1-4 INSPECTION, IAW OPERATOR REQUEST WE INSPECTED THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND A SINGLE BROKEN WIRE. REMOVED CABLE AND PREFORMED LOOP TEST AND FOUND SEVERAL MORE BROKEN WIRES. PRIOR TO DISASSEMBLY THE CABLE TENSION, WAS WITHIN MM LIMITS. INSPECTED CABLE ROUTING AND PULLEYS, ALL CHECKED GOOD. AN SCR HAS BEEN SUBMITTED UNDER NR 246824.
WHILE IN FLIGHT AILERON HAS 3 TO 4 INCHES OF FREE PLAY WITH NO EFFECT ON MOVEMENT OF AILERONS.
DURING ROUTINE PHASE INSP. 1-4 HAD TO REMOVE RT IB LE FOR ANOTHER PROBLEM (REF SCR NR 156504) BEFORE REINSTALLATION OF REPAIRED LE INSPECTED AREA AND FOUND THE HEAT SHIELD/ VAPOR BARRIER PN 6621281-30 CRACKED ON LOWER ATTACH FLANGE 4 FT 2 IN LONG. A CAUSE DUE TO MFG/ASSY ISSUES. FIRST BEING HEAT SHIELD ATTACH FLANGE NOT BEING BENT ENOUGH OR TOO MUCH. WHICH PUTS SHIELD IN A BIND WHEN SANDWICHED BY LE AND WING SKIN ATTACH FLANGE. THE SECOND ISSUE BEING THAT THE WING SKIN ATTACH FLANGE EDGE IS CUT SQUARE AND NOT RADIUSED ON THE CONTACT EDGE. THE CRACK IS NOT ON THE HEAT SHIELD/VAPOR BARRIER FLANGE BEND RADIUS BUT BACK ABOUT .5000 INCH.
FOUND LT AND RT IB LE SKIN WHERE IT JOINS CUFF SKIN RIVETS FOUND COCKED IN HOLES WITH HEAD COCKED ABOVE SURFACE. TO REPLACE RIVETS THE LE HAD TO BE REMOVED, UPON REMOVAL, NOTICED DIFFUSER WAS CRACKED 2 PLACES AND KRINKLED IN 2 PLACES WITH A LITTLE BROWNING ON PRIMER. CRACKS WENT VERTICAL AND WERE 1.0 INCH LONG. SINCE AC WAS IN FOR AN INSP, THE PART WAS REPLACED WITH NEW. .
WHILE PERFORMING NJA'S ONE TIME INSPECTION OF THE HYDRAULIC/PNEUMATIC LINES IN THE WHEEL WELLS, FOUND THE RT EMERGENCY BRAKE LINE CHAFFED THROUGH, THE LT EMEGENCY BRAKE LINE, LT AND RT HAND FLAP RETRACT AND EXTEND LINES, SPEED BRAKE RETRACT AND EXTEND LINES CHAFFED BEYOND LIMITS. - REMOVED AND REPLACED DEFFECTIVE HYDRAULIC AND PNEUMATIC LINES IAW MM CH 27-51-00 AND 32-42-09, SYSTEM OPS AND LEAK CHECKED GOOD.