N347QS
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
DURING DESCENT AT APPROXIMATELY FL 250 AND 280 KIAS A LOUD BUZZ/HUMM BEGAN. IT CONTINUED THROUGH DESCENT OFF AND ON UNTIL AIRSPEED WAS REDUCED BELOW 200 KIAS. STANDING IN THE MID CABIN THE VIBRATION COULD BE FELT ON THE FLOOR AND CABIN TABLES. REMOVED AND REPLACED LH INBD FLAP SHROUD 532AT IAW MM 57-54-00-000-801. PANEL STILL NEEDS SEALED AND PAINTED. P.O.O. OLD/NEW PN: 505-11873-417. SEALED PANEL IAW EMB300 MM 57-54-00-000-801. SEALANT CURE CHECKS GOOD. MCC HAS ELECTED TO CFI THE PAINT.
EMERGENCY LIGHTS REMAIN ON AT ALL TIMES WITH THE COCKPIT SWITCH IN THE ARM POSITION. REPLACED BATTERIES. OPS CHECK GOOD. IAW PHENOM 300 AMM 33-52-01
AS WE APPROACHED THE AIRCRAFT TO BEGIN PREFLIGHT WE NOTICED THE EXTERIOR EMER LIGHTS AT THE RIGHT WING ROOT WERE FLICKERING. UPON OPENING THE CABIN DOOR, ALL THE INRERIOR EMER LIGHTS WERE DISCOVERED IN THE SAME FLICKERING STATE OPS CHECKED EMERGENCY LIGHTING SYSTEM AND FOUND SATISFACTORY AT THIS TIME, PER MCC COMPLETED TASK CARD TC-505÷33-200403
BRK FAIL YELLOW CAS: AFTER POWER UP WE DISCONNECTED THE GPU LIKE NORMAL AND RAN THE AFTER START CHECKLIST. WE RELEASED BRAKE TO TAXI FORWARD, AND MADE IT ABOUT 5 FT BEFORE THE BRAKE FAIL CAS ILLUMINATED. CONFIRMED NO PEDAL PRESSURE. WE THEN USED THE PARKING BRAKE TO STOP THE AIRCRAFT. CORRECTIVE ACTION: REPLACED BCM. OPS CHECK GOOD. IAW AMM 32-41-17.
A-I WINGSTB FAIL YELLOW CAS: CLIMBING OUT OF KTUL A-I WINGSTAB FAIL CAS ILLUMINATED. RAN QRH, MESSAGE PERSISTED, PERFORMED TROUBLESHOOTING AND CHECKS. OPS CHECK GOOD. IAW PHENOM 300 AMM TASK 36-00-00-710-S01-A
AFTER TAKEOFF WE RECEIVED FLAP FAIL CAS. FLAPS FAILED IN THE NUMBER 1 POSITION AND DID NOT RETRACT TO 0. WE ACCOMPLISHED THE QRH PROCEDURE AND CYCLED THE FLAPS AND THE FLAPS STAYED AT FLAPS 1. LANDED WITH FLAPS 1 IN TEB. CORRECTIVE ACTION: GAINED ACCESS TO AIRCRAFT ON RAMP AND OBSERVED FLAP SLIGHTLY EXTENDED AND FLAP LEVER IN THE #1 POISITON. POWERED UP AIRCRAFT AND OBSERVED NO CAS MESSAGES RELATED TO FLAPS PRESENT. MADE SURE FCE BREAKERS WERE CLOSED AND ATTEMPTED TO MOVE FLAPS AND FLAP LEVER INTO THE "O" DETENT. FLAPS DID NOT MOVE AND WE RECIEVED AN AMBER "FLAP FAIL" MESSAGES. CMC CARD WAS NOT PRESENT IN THE AIRCRAFT AND HAD TO POWER DOWN AND CREATE A NEW CMC CARD. POWERED AIRCRAFT BACK UP WITH CMC CARD INSTALLED AND CHECKED CMC MAINTENANCE PAGE, AND SAW FCS FCE 1/PWR DRIVE UNIT FAIL. ATTEMPTED TO RESET FCE #1 AND SET FLAP LEVER TO "O" MULTIPLE TIMES WITH NO SUCCESS. POWERED DOWN AND REAPPLIED POWER AFTER AIRCRAFT WAS MOVED INTO HANGAR AND WAS ABLE TO RESET FCE #L AND SET FLAPS TO "O", PERFORMED NUMEROUS FLAP OPS CHECKS GOING FROM "O" TO "FULL" POSITIONS WITH NO FAILS. RESET POWER AND PERFORMED MULTIPLE SUCCESSFUL OPS CHECKS. GAINED ACCESS TO FCE #L CONNECTOR P0925 AND FLAP PDU CONNECTOR P0919 AND PERFORMED CONTINUITY CHECKS PER PHENOM FIM REF'S 27÷53-00-810-814-A & 27-53-00-810-812-A WITH NO DEFECTS NOTED. RECONNECTED BOTH CONNECTORS AND RE-PERFORMED MULTIPLE FLAPS OPS CHECK PER PHENOM 300 AMM REF. 27-50-00-710-801-A, ALL OPS CHECKS GOOD AT THIS TIME. CLOSED ACCESS PANEL 194EL PER PHENOM AMM REF. 27-51-07. CONTACTED MCC WITH FINDINGS AND ARE AWAITING A RESPONSE. ACCESS TO FCE'S IN LAV ARE OPEN AND HANDWARE ON LAV COUNTER. / PER MCC SWAPPED FCE 1 WITH FCE 2 IAW EMB 505 AMM 27-03-01. PERFORMED OPERATIONAL TEST OF FLAP SYSTEM SEVERAL TIMES. ALL OPS CHECK WERE FOUND SATISFACTORY. CONTACTED MCC WITH FINIDINGS. THEY WERE OK WITH RELEASING AIRCRAFT BACK TO SERVICE. ALL WORK ACCOMPLISHED !AW EMB 505 AMM 27-51-07.
DURING DESCENT, NOTIFIED BY PAX THE EMERGENCY LIGHTS FLICKERING ON & OFF . LIGHT SWITCH WAS CYCLED & AFTER A FEW SECONDS, BEGAN FLICKERING AGAIN WITH SWITCH IN ARM. PERFORMED TC-FLT-33-1001. FOUND WITH BOTH BATTERIES CONNECTED, ALL EMERGENCY LIGHTS WOULD START TO FLICKER WITHIN APPROX 5 MINS. FOUND THE NR1 BATTERY ALLOWED THE LIGHTS TO FLICKER APPROX 5 MINS AFTER LIGHT SWITCH WAS PLACED TO ON. FOUND THE NR 2 BATTERY ALLOWED THE EMERGENCY LIGHTS TO ILLUMINATE & FLICKER IMMEDIATELY WITH SWITCH IN ARM. REMOVED FAULTY NR 1 FWD BATTERY & INSTALLED REPAIRED BATTERY IAW MM 33-52-01. REMOVED FAULTY NR 2 BATTERY & INSTALLED REPAIRED BATTERY IAW MM 33-52-01. PERFORMED OPS TEST IAW MM 33-52-01, NO DEFECTS NOTED.
TAPPING/GURGLING NOISE FROM PILOT SIDE FLOOR AREA & POOLING WATER IN FLOOR VENTS. MOLDY MILDEW ODOR FROM COCKPIT & CABIN. CONDENSATION TRAPPED AT FLOOR VENTS & PILOT GASPER GURGLING. VACUUMED MOISTURE & RAN HEAT AT MAX UNTIL ALL CONDENSATION WAS DRY. PILOT GASPER NOT GURGLING & NO MOISTURE AT FLOOR VENTS. COCKPIT STILL HAS MOLDY ODOR. AMM 21-52-03 EVAP MODULE ASSY· INSPECTION/CHECK. COVER PANEL DAMAGED & HARDWARE IS STRIPPED. EVAPORATOR FINS LOOK CLEAN, MANY DISTORTED OR FLAT. REMOVED FWD EVAP UNIT IAW AMM 21-52-03. WATER IN AREA, VACUUMED. INSTALLED NEW EVAP. REPLACED DAMAGED FWD EVAP PANEL & HARDWARE. REPLACED RECEIVER DRYER. RECHARGED FREON SYS, LEAK & OPS CHECKS, NO DEFECTS. WORK DONE IAW AMM 21-52-03.
MAIN DOOR HARDWARE: SILVER PART (MARKED PUSH) OF THE EXTERNAL DOOR HANDLE DOES NOT SPRING INTO THE FLUSH POSITION AFTER USE, INSTEAD IT REMAINS LOOSE AND HANGING INTO THE AIRSTREAM. R & R SPRING PN 50-10076-001. WORKED PERFORMED WITH REF TO THE PHENOM 300 AMM 52-10-00. OPS CHECK PERFORMED WITH NO DEFECTS NOTED AT THIS TIME.
WHILE COMPLYING WITH SB 505-55-0004 FOUND THE FOLLOWING FLIGHT CONTROL BALANCE WEIGHTS NOT ACCEPTABLE PER SB AND REPLACED WITH NEW PARTS. ONE LT ELEVATOR HORN WEIGHT P/N PE915109-L42, SEVEN LT ELEVATOR ADJUSTABLE WEIGHTS P/N PE915109-L33, ONE RT ELEVATOR HORN WEIGHT P/N PE915109-L42, TEN RT ELEVATOR ADJUSTABLE BALANCE WEIGHTS P/N 915109-L33, TWENTY FOUR ADJUSTABLE RUDDER BALANCE WEIGHTS P/N PE915109-L27, AND ONE LT AILERON BALANCE WEIGHT P/N PE915109-L31.
DURING CLIMB, FELT AN ABNORMAL VIBRATION. WHILE RUNNING ENGINE ABNORMAL VIBRATION CHECKLIST, THE VIBRATION INCREASED AND GEN 2 OFF BUS MESSAGE DISPLAYED, AND GEN 2 VOLTAGE DROPPED RAPIDLY. RAN GEN 2 OFF BUS CHECKLIST, WHICH DIRECTED ENGINE SHUTDOWN. VIBRATION CONTINUED TO INCREASE IN AMPLITUDE DURING SHUTDOWN. AFTER SHUT DOWN VIBRATION MOSTLY WENT AWAY OCCASIONALLY FELT A FLUTTER. POST-FLIGHT INSPECTION REVEALED HEAVY SOOT ON BOTTOM OF THE NR 2 NACELLE. ENGINE WAS WINDMILLED FOR 20 MINUTES. REPLACED THE NR 2 ENGINE STARTER GENERATOR
CAPT PFD CONTROLLER EJECTED FROM PANEL ON TAKEOFF. TAKEOFF DISCONTINUED SECURED CONTROLLER, OPS CHECK GOOD WORKED IAW MM CH 34-23-02.
CAPTAIN PFD CONTROLLER EJECTED FROM PANEL ON TAKEOFF. TAKEOFF DISCONTINUED. (S)
DURING A PHASE 1-4 INSPECTION, FOUND THE MASTER CYLINDER ATTACH BRACKET MOUNT HOLES GOUGED DURING INSTALLATION AT THE FACTORY, UPON FURTHER INSPECTION FOUND A .7500 INCH CRACK IN THE FLANGE ATTACH LEG RADIUS. REPLACED WITH NEW BRACKET ASSY. SUBMITTED SCR TO MFR UNDER SCR NR 301844.
RH MAIN GEAR LIGHT WOULD NOT ILLUMINATE AFTER 2 CYCLES OF LANDING GEAR. AFTER GO AROUND AND VERIFICATION FROM TOWER WAS RECEIVED, RIGHT HAND GEAR LIGHT ILLUMINATED. NO OTHER INDICATIONS THAT GEAR WAS NOT DOWN ADN LOCKED EXISTED. ROTARY TEST REVIELD THAT THE BULB WAS NOT INOP. AS A PRECAUTION, EMERG GEAR EXT WAS ACCOMPLISHED AND NITROGEN BACK UP WAS ACTIVATED. REMOVED RT MAIN LANDING GEAR ACTUATOR AND INSTALLED REPAIRED MAIN LANDING GEAR ACTUATOR IN THE R/H POSITION. PERFORMED GEAR OPERATIONAL CHECK. ALL CHECKS WERE GOOD. ALL WORK DONE I.A.W. CESSNA 560 ULTRA AMM 32-31-04
DURING GEAR EXTENSION , DID NOT ACHIEVE A GREEN( LOCKED INDICATION) ON THE RIGHT MAIN GEAR. RAN THE GEAR WILL NOT EXTEND CHECKLIST. GEAR WAS DOWN BUT NOT LOCKED. ACHIEVED A GREEN LIGHT AS RESULT OF CHECKLIST. JACK A/C DEPLETED NITROGEN IN LANDING GEAR, LUBE AND INSPECTED RT MAIN GEAR, SERVICED EMERGENCY NITROGEN BOTTLE, RAN GEAR 10X AND MORE OPS AND LEAK CHECK GOOD ALL WORK DONE IAW CE560 M/M 32-30-00.
(CABIN DOOR) ANNUNICATOR ILLUMINATED DURING T/O AT 70 KNOTS. ABORTED T/O ROLL. ADJUSTED MAIN CABIN DOOR LOCK SWITCH. OPS CHECKS GOOD IAW MM 52-70-01.
RT ENGINE ITT REACHED 730 DEGREES (C) FOR APPROX 3 SECONDS DURING TAKEOFF ROLL; TAKEOFF ABORTED. N1 WAS EXACTLY AT TARGET FOR CONDITIONS. REMOVED AND REPLACED BOV SOLENOID ON RT ENGINE. OPS CHECK GOOD. WORK DONE IAW CH 72-30-07, 73-20-01, AND 73-10-12 OF THE MM.
DURING FLIGHT, MODERATE ELECTRICAL ODOR IN CABIN, ESPECIALLY ALONG CEILING AREA NEAR DOOR. NO VISIBLE SMOKE. ODOR DISAPATED DURING DESCENT. CONDITIONS: FL400, NIGHT, VMC, CABIN LIGHTING ON, DIVERTED TO GSO. UNABLE TO DUPLICATE DISCREPANCY AT THIS TIME, REMOVED COALESER SOCK AND CLEANED, NO DEFECTS NOTED, REMOVED CABIN OVERHEAD AND VERIFIED ELECTRICAL CONNECTIONS, NO DEFECTS NOTED. ALL WORK DONE MM 21-20-00.
DURING DESCENT, WINDSHIELD HEAT WAS SELECTED TO LOW, AFTER OPENING THE WINDSHIELD BLEED KNOBS. APPROX 1 MINUTE LATER AN ODOR WAS OBSERVED FOLLOWED BY THE -WINDSHIELD AIR OVERHEAT- ANNUNCIATOR. TURNED SYSTEM OFF, SMELL AND LIGHT WENT AWAY. RAN AC, RAN WINDSHIELD HEAT FOR SEVERAL MINUTES, OPERATIONAL CHECK OF WINDSHIELD BLEED AIR ANTI-ICE CHECKED GOOD. COULD NOT DUPLICATE ODOR OR -WINDSHIELD AIR OVERHEAT- ANNUNCIATOR. ALL WORK PERFORMED IAW CESSNA 560 ULTRA MM CH 30-41-00. NO OTHER DISCREPANCIES NOTED.
ON TAKEOFF, RIGHT MAIN GEAR WOULD NOT COME UP (HANDLE DID). FOUND ACTIVATING SIDE OF RT UPLOCK SWITCH BAD. REMOVED AND REPLACED SWITCH IAW 560M/M CHPT 32-31-05. ADJUSTED SWITCH IAW CE-560 CHPT 32-61-00. PERFORMED LANDING GEAR FUNCTIONAL CHECK, AND DOWNLOCK, UPLOCK PARALLELING CIRCUIT TEST. PERFORMED LANDING GEAR TIMED CYCLE TEST IAW CE-560 M/M CHPT 32-01-00. OPERATIONAL CHECKS SATISFACTORY.