N527QS
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
A VIBRATION IS FELT ON THE FLOOR AND HEARD WITH AND WITHOUT HEADSETS AT ALL ALTITUDES AND AIRSPEEDS INTERMITTENTLY THROUGHOUT A FLIGHT. AVIONICS FAN IS SUSPECT. WHILE NLG IN STOWED POSITION, RT DOOR AFT SIDE OVERLAPPING NOSE SKIN BY .20. TRIMMED RT NLG DOOR, . CYCLED GEAR TO VERIFY DOOR CLEARANCE. CLEARANCE CHECK GOOD. ACCOMPLISHED WORK IAW MM CH. 52-10-00. WITH NLG IN STOWED POSITION, RT NLG DOOR AFT EDGE IS .18 INCH INTO AIRSTREAM. EXCESSIVE PLAY FOUND AT RT MLG DOOR.
FUSELAGE STRUCTURE: DURING CRUISE FLIGHT THERE IS AN INTERMITTENT VIBRATION FELT IN THE FLOOR AS WELL AS AN AUDIBLE SOUND FROM THE VIBRATION. THE CYCLE ISN'T RHYTHMIC AND YOU CAN'T PREDICT WHEN IT WILL RETURN. IT LASTS FOR ROUGHLY 30 SECONDS. IT SOUNDS LIKE A FAN OPERATING BUT FEELS LIKE ITS COMING FROM THE GEAR AREA. CORRECTIVE ACTION; FOUND LH NLG DOOR TO HAVE MORE MOVEMENT THAN RH NLG DOOR. NLG STOP BOLTS ON LH DOOR CONTACTING LATER THAN RH DOOR. PERFORMED NLG DOOR ADJUSTMENT/TEST IAW 680A MM 52-80-05.
MAIN DOOR: IT IS VERY DIFFICULT TO SEE THE PINS ON THE MAIN CABIN ENTRY DOOR THROUGH THE VIEWING PORTS. CORRECTIVE ACTION: CLEARED DUST FROM MIRRORS. OPS CHECKS GOOD AT THIS TIME.
LAV EXIT SIGN/LIGHT: DURING POWER ON CHECKLIST EMER LTS-ARM, EMERGENCY EXIT SIGN ON BULKHEAD BEHIND SEAT 7 DID NOT ILLUMINATE. COMPLIED WITH OPS CHECKING EMER LIGHT SYSTEM SEVERAL TIMES OPS CHECK GOOD. INSPECTED LH AFT DIVIDER AND LIGHT FOUND NO DEFECTS . COMPLIED WITH CYCLING POWER AND OPS CHECKING EMER LIGHT SYSTEM EVEN GOING BACK AND SHAKEING AFT DIVIDER AND BANGING ON IT TO SEE IF I COULD MAKE LIGHT FAIL OPS CHECK GOOD ALL WORK DONE IAW CE 680A AMM 33-50-00.
DURING FLIGHT AT HIGH & LOW SPEED, WAS A SIGNIFICANT BINDING IN YOKE FWD OF NEUTRAL POSITION FOR ELEVATORS. PERFORMED VISUAL INSPECTION OF ELEVATOR HINGES & ATTACH HARDWARE, NO DEFECTS. VERIFIED FREEDOM OF MOVEMENT OF ELEVATORS GOOD. PERFORMED GVI OF THE AFT ELEVATOR SECTOR, DOWN SPRINGS, FWD & AFT ROD ENDS, SAFTEY WIRE & LOCKING WASHER TABS. NO DEFECTS. GVI OF UPPER ROD ENDS BOLTS, ELEVATOR BELLCRANK & LOCKING WASHERS & SAFTEY WIRE. NO DEFECTS. INSPECTED YOKE COLUMN & BELOW FLOOR FOR OBSTRUCTIONS & FREEDOM OF MOVEMENT, GOOD. ISOLATED LT & RT ELEVATORS PITCH/ROLL DISCONNECT, FREEDOM OF MOVEMENT GOOD. COULD NOT DUPLICATE BINDING. PERFORMED IAW MM 27-30-00. ACFT OK FOR RETURN TO SERVICE.
TRIM NOSE DOWN AMBER CAS DISPLAYED WHILE AT 16,000 FT, 300 KIAS WITH AUTO-PILOT ENGAGED. WHEN AUTO-PILOT DISENGAGED, SIGNIFICANT FWD PRESS REQUIRED TO MAINTAIN LEVEL FLT & PITCH TRIM DISPLAY INDICATED AT ND LIMIT & 1.2. AT 260 KIAS, PRESS FELT NORMAL BUT PITCH TRIM INDICATED AT ND STOP. REMOVED BOLT FROM PRIMARY STAB TRIM ACTUATOR. BOLT IS TEMPED INSTALLED. SNAP RING ATTACHED TO SLEEVE NEEDS REPLACED IAW AMM 27-40-00. TURNED HORIZ TRIM ACTUATOR 7 TURNS COUNTERCLOCKWISE IAW AMM 27-40-00. RECEIVED & REMOVED TEMP INSTALLED HORIZ STAB ACTUATOR SLEEVE & BOLT IAW AMM 27-40-05. PREFORMED HORIZONTAL STAB TRIM RIGGING IAW AMM 27-40-00. OPS CHECKED HORIZONTAL STAB, NO DEFECTS. OPS CHECKS GOOD.
MAIN EXIT SIGN/LIGHT: EMER LIGHT STAYS ON EVEN WITH THE POWER OFF AND BATTERIES DISCONNECTED // SIGNOFF // CONNECTED BATTERLES AND GAIN ACCESS TO COCKPIT. FOUND FOUND MAIN DOOR OVERHEAD AND FORWARD ISLE EMERGENCY LIGHT ILLUMINATED. GAINED ACCESS TO FORWARD INERTIA SWITCH AND DEPRESSED. BOTH EMERGENCY LIGHTS TURNED OFF. ENGAGED BATTERLES AND STARTED APU. CHARGED EMERGENCY BATTERIES FOR 30 MINUTES. TURNED OFF APU AND DISENGAGED BATTERY POWER. TURNED EMERGENCY LIGHT ON AND WALTED 10 MINUTES. EMERGENCY LIGHTS STAYED ILLUMINATED FOR DURATION. ENGAGED BATTERIES AND STARTED APU CHARGE EMERGENCY BATTERIES FOR 45 MINUTES. WORK PERFORMED IAW CE-680A AMM 33-50-00. OPS CHECK GOOD.
RIGHT MLG LANDING GEAR RETRACTION: AFTER SELECTING THE GEAR UP, A AMBER X DISPLAYED ON THE RIGHT MAIN GEAR ALONG WITH A GEAR DISAGREE R APPEARED AS A AMBER CAS MESSAGE. // SIGNOFF// ARRIVED AT AIRCRAFT, REMOVED RH MLG DOWN LOCK SWITCH PN: 6-0373-3 DUE TO BEING INOP. INSTALLED CUSTOMER SUPPLIED NEW DOWN LOCK SWITCH. REMOVED FUSELAGE PANEL 316AR TO GAIN ACCESS TO LANDING GEAR CONTROL MANIFOLD TO RESET THE PNEUMATIC OVERRIDE VALVE. RESET THE EMERGENCY GEAR EXTENSION PNEUMATIC CONTROL CABLE AND VALVE ON BOTTLE. SERVICED EMERGENCY GEAR BLOW DOWN ACCUMULATOR TO PROPER PRESSURE. CONNECTED HYDRAULIC MULE AND PERFORMED 10 GEAR SWINGS FOR OPS CHECK AND TO BLEED THE HYDRAULIC SYSTEM. ONCE OPS CHECKS WERE COMPLETED. PERFORMED EMERGENCY LANDING GEAR EXTENTION SYSTEM TEST. AFTER TEST COMPLETE RESET LANDING GEAR PNEUMATIC OVERRIDE VALVE AND EMERGENCY PNEUMATIC CONTROL CABLE AND VALVE. PERFORMED 10 MORE GEAR SWINGS TO BLEED THE SYSTEM. ONCE ALL SYSTEM CHECKS AND OPS CHECKS COMPLETE REINSTALLED ACCESS PANEL 316AR AND INSTALLED COPPER SAFETY WIRE ON EMERGENCY PNEUMATIC GEAR BLOW DOWN CONTROL CABLE. DOWN JACKED AIRCRAFT AND RESET FLIGHT HOUR METER CB. ALL WORK WAS DONE IAW CE-680A AMM 32-30-15, 32-34-00 AND 12-10-45.
EMERGENCY LIGHTING: THE EXIT SIGN OVER THE MAIN CABIN DOOR AS WELL AS THE STRIP LIGHT UNDER SEAT 10 REMAIN ON WITH THE EMER LTS SW IS IN THE OFF POSITION. ALL OTHER EMER LIGHTS EXTINGUISH NORMALLY. //SIGNOFF// GAINED ACCESS TO AIRCRAFT. ONCE MAIN ENTRY DOOR OPENED, NOTICED EMERGENCY LIGHTS WHERE ON, REVIEWED SCHEMATICS AND WIRING DIAGRAMS REFERRING TO EMERGENCY LIGHTING. THE FORWARD EMERGENCY LIGHTS THAT ARE STUCK ON ARE ASSOCIATED WITH THE #1 EMERGENCY BATTERY. LOCATED BATERYTO ENSURE CANNON PLUG AND/OR ANY ASSOCIATED WIRING WAS NOT SHORTED OPEN. NO FAULTS NOTED. REMOVED COCKPIT CENTER CONSOLE PANELS TO LOCATE #1 EMERGENCY LIGHTING INERTIA SWITCH. SWITCH APPEARED TO BE TRIPPED. RESET SWITCH AND EMERGENCY LIGHTS EXTINGUISHED WITH REF TO CE680A MM 33-50-06 LEFT EMERGENCY LIGHTS IN ARM TO CHARGE BATTERY FOR SOME TIME. RETURNED AIRCRAFT TO ORIGINAL CONFIGURATION.
LANDING NORMAL, AFTER TOUCHDOWN & APPLYING NORMAL BRAKING & THRUST REVERSING, ACFT BEGIN VEERING OFF CENTERLINE RIGHT. LT BRAKE PEDAL SEEMED TO BE FLAT, NO PRESS & NO BRAKING. RELEASED BRAKE PEDALS & USED T/R & TILLER TO REGAIN CENTERLINE. AFTER FAILURE, AMBER ANTISKID FAIL LIGHT ILLUM. AFTER SOME DISTANCE, AMBER LIGHT EXTINGUISHED & BRAKING NORMAL. MANUFACTURER ADVISED OUTBOARD BRAKE PRESSURE READING HIGH & INBD BRAKE PRESSURE BELOW 100 PSI. MANUFACTURER ADVISED TO CHECK ANTI SKID WIRING INBD & OTBD LT BRAKES. RANG OUT WIRING FOR WHEEL SPEED TRANSDUCERS & FOUND CONNECTORS TO BE REVERSED IAW WIRING DIAGRAM 32-40-01, FIGURE 1. CORRECTED, OPS CHECKED GOOD IAW MM 32-46-05.
APU BLEED AIR: AFTER NORMAL STARTUP WHEN APU BLEED AIR SELECTED SMOKE FILLED THE CABIN AND COCKPIT (PER CREW, POST FLIGHT, NO PAX ON BOARD) // SIGNOFF// REPLACED APU WITH REPAIRED APU IAW CESSNA 680A AMM TASK-49-10-00, REFER TO 15,1 FOR LEAK AND OPS CHECKS, REMOVED P/N-3800785â¢1 S/N-P-814 INSTALLED P/N-380078S-1 S/N-P-763
MAIN DOOR HANDLE: REPEAT WRITE UP, NUMBER 2. REFERENCE THE WRITE UP ON 08/02/2022. MAIN DOOR HANDLE WILL NOT MOVE IN ORDER TO LATCH DOOR. NEITHER OUTSIDE OR INSIDE HANDLE WORK.//CORRECTIVE ACTION//GAINED ACCESS TO MCD LATCH/LOCK SYSTEM BY REMOVING STEP ASSEMBLY. VISUALLY INSPECTED MCD LATCH/LOCK SYSTEM. NOTED "PUSHROD 4 ", PUSHROD FROM THE HANDLE ASSEMBLY TO THE FWD UPPER LATCH PIN IS OUT OF ADJUSTMENT, AND THE HANDLE FULL OPEN STOP OUT OF ADJUSTMENT. ADJUSTED "PUSHROD 4" A HALF TURN IN TO WITHIN LIMITS AND ADJUSTED HANDLE FULL OPEN STOP OUT TO WITHIN LIMITS. WORK DONE I/A/W CE 680A M/M CHAPTER 52-10-04. PERFORMED SEVERAL OPERATIONAL CHECKS. OPERATIONAL CHECKS ARE SATISFACTORY. NO DEFECTS NOTED. CLOSED ACCESS TO MCD
MAIN DOOR HANDLE: MAIN DOOR HANDLE WILL NOT MOVE IN ORDER TO LATCH DOOR. NEITHER INSIDE OR OUTSIDE HANDLES WORK.//CORRECITVE ACTION//REMOVED AND REPLACED FORWARD LOWER LATCH/LOCK ASSEMBLY. PN: 7411311-70. REF CE680A MM 52-10-09. DOOR OPS CHECK GOOD.
RIGHT MLG LANDING GEAR EXTENSION: DURING FLIGHT AT 4000' 250 KIAS IN CONTINUOUS CHOP SPEED TAPE TURNED RED AND AUTO THROTTLES REDUCED TO 210 THREE TIMES DUE TO RIGHT GEAR MONENTARILY INDICATING NEITHER UP NOR DOWN. THERE WAS NO NOTICABLE INCREASE IN NOISE NOR FEELING OF THE GEAR MOVING IN THE WELL. AINED ACCESS AND REMOVED OLD SWITCH 1/A/W MODEL 680A MAINTENANCE MANUAL (REV 12) 32-32-25 (ORIGINAL ISSUE) MAIN GEAR UPLOCK SWITCH - REMOVAL/INSTALLATION AND INSTALLED ONE EACH NEW SWITCH P/N 6948101-3, NSN IAW MODEL 680A MAINTENANCE MANUAL (REV 12) 32-32-25 (ORIGINAL ISSUE) 1 MAIN GEAR UPLOCK SWITCH - REMOVAL/INSTALLATION. OPS CHECK GOOD
MAIN EXIT SIGN/LIGHT: AFTER FLIGHT WITH AIRCRAFT POWERED DOWN EMERGENCY EXIT LIGHT OVER MAIN CABIN DOOR REMAINS ON.///REMOVED AND REPLACED COCKPIT, FWD AND AFT CABIN, AND AFT CLOSET EMERGENCY LIGHT POWER SUPPLIES WITH REPAIRED CUSTOMER SUPPLIED PARTS WITH REF CE680A MM 33-50-06. OPS CHECK GOOD
ALL LANDING GEAR RETRACTION DID NOT RETRACT - LANDING GEAR WILL NOT RETRACT ***CORRECTIVE ACTION*** INSPECTED AIRCRAFT FOUND BLOW DOWN BOTTLE SHEAR WIRE-BROKEN. GAINED ACCESS TO LANDING GEAR CONTROL VALVE, AND FOUND THAT THE EMERGENCY EXTENSION ROD WAS DEPLOYED ON THE VALVE, FURTHER INDICATING GEAR WAS BLOWN DOWN. CONTACTED MCC, AND WAS ADVISED TO CHANGE THE LANDING GEAR HYD MANIFOLD DUE TO PRECAUTION, AND THE ADVISE, FSR FOR TEXTRON. ALSO, CHECKED INPUTS TO PINS 4 AND-5 AT- PYO 13 TO CONFIRM RETRACT SOLENOID WAS GETTING-PROPER SIGNAL FROM PCB'S. RESET EMERGENCY BOTTLE DEPLOYMENT ARM AS REQUIRED. ACCESSED MANIFOLD AND REMOVED FAULTY MANIFOLD PIN VIOOOOAOI2, SIN 0900. REPLACED MANIFOLD WITH OVERHAULED UNIT PIN VLOOOOA012?? SIN 0963. COMPLIED WITH SEVERAL SATISFACTORY GEAR SWINGS TO COMPLY WITH THE BEGINNING OF BLEED PROCEDURES. AT THIS POINT, LANDING GEAR BREAKOUT BOXES ARE REQUIRED TO COMPLETE THE-REQUIRED HYDRAULIC BLEEDING/OPS CHECKS. WORK WITH REF. TO CE680A MM CHAPT. 32-34-00, 32-30-20. RECEIVED-TOOLING: COMPLIED-WITH THE-REMAINING-BLEEDING PROCEDURES AS REQUIRED PER CE680A MM CHAPT. 32-30-20, 32-34-00, 12-10-30. NO FURTHER DEFECTS NOTED AT THIS TIME. (NOTE, UNIQUE CONTROL #CORRECTION ONLY)
ALL LANDING GEAR RETRACTION DID NOT RETRACT - LANDING GEAR WILL NOT RETRACT ***CORRECTIVE ACTION*** INSPECTED AIRCRAFT FOUND BLOW DOWN BOTTLE SHEAR WIRE-BROKEN. GAINED ACCESS TO LANDING GEAR CONTROL VALVE, AND FOUND THAT THE EMERGENCY EXTENSION ROD WAS DEPLOYED ON THE VALVE, FURTHER INDICATING GEAR WAS BLOWN DOWN. CONTACTED MCC, AND WAS ADVISED TO CHANGE THE LANDING GEAR HYD MANIFOLD DUE TO PRECAUTION, AND THE ADVISE FSR FOR TEXTRON. ALSO, CHECKED INPUTS TO PINS 4 AND-5 AT- PYO 13 TO CONFIRM RETRACT SOLENOID WAS GETTING-PROPER SIGNAL FROM PCB'S. RESET EMERGENCY BOTTLE DEPLOYMENT ARM AS REQUIRED. ACCESSED MANIFOLD AND REMOVED FAULTY MANIFOLD PIN VIOOOOAOI2, SIN 0900. REPLACED MANIFOLD WITH OVERHAULED UNIT PIN VLOOOOA012?? SIN 0963. COMPLIED WITH SEVERAL SATISFACTORY GEAR SWINGS TO COMPLY WITH THE BEGINNING OF BLEED PROCEDURES. AT THIS POINT, LANDING GEAR BREAKOUT BOXES ARE REQUIRED TO COMPLETE THE-REQUIRED HYDRAULIC BLEEDING/OPS CHECKS. WORK WITH REF. TO CE680A MM CHAPT. 32-34-00, 32-30-20. RECEIVED-TOOLING: COMPLIED-WITH THE-REMAINING-BLEEDING PROCEDURES AS REQUIRED PER CE680A MM CHAPT. 32-30-20, 32-34-00, 12-10-30. NO FURTHER DEFECTS NOTED AT THIS TIME.
RIGHT HORIZONTAL STAB DAMAGED - RIGHT LEADING EDGE HORIZONTAL STAB APPEARS DAMAGED AT THE TIP. ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DQ1922M1 DATED APRIL 17, 2019; 680A-0069 (N527QS) HORIZONTAL STABILIZER RIGHT TIP CAP DAMAGE (EROSION).
DURING CHECKLIST DAMAGE WAS FOUND TO COMPOSITE PANELS ON UNDERSIDE OF AFT FUSELAGE AREA. ACCOMPLISHED AQRD ENGINEERING REPAIR ORDER NO. ERO-103261 DATED APRIL 15, 2019; BELLY AND WHEEL BIN FAIRINGS - PERMANENT REPAIR.
RIGHT HORIZONTAL STAB DAMAGED- RIGHT LEADING EDGE HORIZONTAL STAB APPEARS DAMAGED AT THE TIP. ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DQ1922M1 DATED APRIL 17, 2019; 680A-0069 (N527QS) HORIZONTAL STABILIZER RIGHT TIP CAP DAMAGE (EROSION).
RIGHT GEAR DISAGREE, AMBER CAS ILLUMINATED INFLIGHT. GEAR DISAGREE RT CAS MESSAGE ILLUMINATED. RIGHT MAIN GEAR INDICATION CHANGED TO CROSSHATCH, IAS TURNED RED, AND AUTO THROTTLE ATTEMPTED TO CORRECT THE PERCEIVED OVER SPEED CONDITION. REMOVED AND REPLACED THE RT MLG UPLOCK SWITCH IAW AMM 32-32-25.