N314QS
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
Maintenance disclosures
FUEL PUMP 1 FAIL YELLOW CAS: AT 400 FEET AGL ON DEPARTURE GOT A FUEL LO PRES CAS, WHICH QUICKLY WENT AWAY AND REPLACED BY A FUEL PUMP 1 FAIL YELLOW CAS AND A FUEL 1 FEED FAULT WHITE CAS. BOTH OF THOSE CAS MESSAGES REMAINED FOR THE REST OF THE FLIGHT AND THE FUEL PUMP 1 FAIL MESSAGE REMAINED AFTER ENGINE SHUTDOWN. CORRECTIVE ACTION; REPLACED #1 FUEL BOOST PUMP AND PRESSURE SWITCH IAW PHENOM AMM 28-21-03 & 28-45-01. OPS CHECK GOOD.
FUEL PUMP 1 FAIL YELLOW CAS: AT 400 FEET AGL ON DEPARTURE GOT A FUEL LO PRES CAS, WHICH QUICKLY WENT AWAY AND REPLACED BY A FUEL PUMP 1 FAIL YELLOW CAS AND A FUEL 1 FEED FAULT WHITE CAS. BOTH OF THOSE CAS MESSAGES REMAINED FOR THE REST OF THE FLIGHT AND THE FUEL PUMP 1 FAIL MESSAGE REMAINED AFTER ENGINE SHUTDOWN.
BRAKE CHECK UPON INTIAL TAXI ROLL CAUSED A CHATTER AND BOUNCING EFFECT UPON BRAKE APPLICATION. HARD TO TELL IF LEFT BRAKE, RIGHT BRAKE OR BOTH. SERVICED HYDRAULIC RESERVOIR. OPS CHECK GOOD. IAW AMM 32-40-00 & AMM 12-13-00.
NLG LANDING GEAR RETRACTION: ON DEPARTURE GEAR FAILED TO RETRACT AFTER GEAR UP SELECTED. RED INDICATION ON ALL 3 GEAR WITH VIBRATION . COMPLETED QRH AND HAD THREE GREEN LIGHTS AFTER GEAR EXTENSION . REMOVED AND REPLACED LDG CONTROL LEVER. OSD: 1/30/2025
LG LEVER DISAG RED CAS: ON RETRACTING THE GEAR AFTER TAKEOFF, LG LEVER DISAG DISPLAYED WITH THREE RED DN INDICATIONS. AN UNUSUALLY LOUD RUMBLING SOUND DURING RETRACTION WAS OUR FIRST ALERT THAT SOMETHING WAS ABNORMAL, SUGGESTING THAT THE INBOARD GEAR DOORS OPENED. UPON CYCLING THE GEAR LEVER BACK DOWN THE CAS MESSAGE EXTINGUISHED WITH 3 GREEN GEAR INDICATIONS. CORRECTIVE ACTION: REPLACED LDG CONTROL LEVER. OPS CHECK GOOD. IAW EMB505 AMM 32-31-01
VENTRAL RUD FAIL WHITE CAS: REPEAT WRITE UP. CAS ILLUMINATED IN FLIGHT, STARTED WITH YELLOW HDG FLAG FOLLOWED BY AP/YD/SWPS FAIL CAS MESSAGE. ALSO RECEIVED AHRS 2 FAIL, CAS MESSAGE CLEARED A FEW MINUTES ADTWR REVERTINF TO AHRS 1 CORRECTIVE ACTION; REPLACED #2 AHRS IAW EMB-505 AMM 34-21-01. PERFORMED SATISFACTORY VENTRAL RUDDER OPS TEST. NO FURTHER DEFECTS NOTED.
DOOR HANDLE PLACED IN THE OPEN POSITION, BUT LOCKING PINS WILL NOT RELEASE. DOOR CAN NOT BE OPENED. UNLOCKED CABIN DOOR AND OPENED AS NORMAL. NOTED WATER AROUND THE DOOR SEAL AND VENT DUE TO HEAVY RAIN THE PRIOR DAY. IT IS SUSPECTED THAT THE DOOR FROZE. NOTE: DOOR PINS ARE WELL LUBED. OPS CHECKED GOOD IAW 52-10-20-801A
RECEIVED IN CONJUNCTION WITH AMBER AHRS 2 FAIL, AP FAIL, & YD FAIL. CORRECTIVE ACTION; POWERED UP AIRCRAFT AND ALLOWED FOR FULL BOOT UP, NO CAS MESSAGES POSTED. SENT CMC FILES TO CONTACT CENTER. CONTACT CENTER REPLIED AND ADVISED TO PERFORM FIM TASK 34Ãâ¬Â¢21Ãâ¬Â¢00Ãâ¬Â¢810-828-A, PERFORMEO FIM TASK AS ADVISED ANO FAULT DID NOT POPULATE, FIM TASK IS CONSIDERING AT TRANSATORY CONDITION, CONTACTED MCC AND RELAYED RESULTS. PERFORMED AUTOPILOT TEST AS RECOMMENDED BY CONTACT CENTER IAW EMB505 MM 22÷11÷00, OPS/CK GOOD. OK TO CONTINUE,
EMER LT NOT ARM YELLOW CAS: EMER LT NOT ARM YELLOW CAS IN FLIGHT. SWITCH IN THE ARM POSITION. INTERIOR EMER LIGHTS ILLUMINATED. CORRECTIVE ACTION: REMOVED INOP COCKPIT LIGHT SWITCH PANEL. IAW PHENOM 300 AMM 33-01-01. OPS CHECK GOOD.
EMERGENCY LIGHTS STAY ON WHEN THE SWITCH IS IN THE ARM POSITION. REMOVED DEFECTIVE EMERGENCY LIGHT BATTERY 1 P/N:7450LS-00 S/N:005253 AND REPLACED WITH CUSTOMER SUPPLIED(REPAIRED) BATTERY P/N:7450LS-00 S/N:006062 PER P-300 AMM 33-52-01. NO DEFECTS NOTED.
EMERGENCY LIGHTING: UPON LANDING OWNERS INFORMED US THE EMERGENCY LIGHTS HAD BEEN FLASHING FOR APPROXIMATLEY 45 MINUTES. I PLACED THE EMER LT SWITCH TO ALL 3 POSITIONS. ANY TIME THEY WERE PLACED IN ARMED OR ON THEY WOULD FLASH LIKE A STROBE. THIS INCLUDES ALL CABIN LIGHTS, AIRSTAIR LIGHTS AND OVER/UNDER WING LIGHTS. ARRIVED AT THE AIRCRAFT, CONNECTED EXTERNAL POWER AND APPLIED POWER TO THE AIRCRAFT. AFTER 90 MINUTES, TURNED ON THE EMERGENCY LIGHTS AND NO FLICKERING WAS NOTED. I TRIED THE LIGHTING IN THE ON POSITION AS WELL AS THE ARMED POSITION NOTING NO FLICKERING AT THE TIME. SHUT DOWN THE GPU & TURNED OFF MAIN BATTERIES & SWITCHED EMERGENCY LIGHTS TO ON IAW AMM 33-52-01-710-801-A. EMERGENCY BATTERY OPS TEST MINUTES NOTING NORMAL OPERATION. CONNECTED A GPU & TURNED ON MAIN BATTERIES & GROUND POWER FOR 2 HOURS TO ENSURE EMERGENCY BATTRERIES WERE CHARGED. PERFORMED THE OPS CHECK OF THE EMERGENCY BATTERIES REFERENCING AMM 33-52-00-710-801-A NOTING NO DEFECTS AT THIS TIME.
CABIN EMERG LIGHT: AT 43,000 ABOUT HOUR INTO FLIGHT CABIN EMERLIGHTING FLICKERING. LOOK AT VIDEO ATTACHMENT. REMOVED AND REPLACED #1 EMERGENCY BATTERY. REMOVED AD REPLACED #2 EMERGENCY BATTERY. PERFORMED SATISFACTORY OPS CHECK. WORK PERFORMED IAW AMM 33-52-01 AND FIM 33-50-00-810-802-A.
EMERG LIGHT SWITCH: EMER LIGHTS REMAIN ILLUMINATED WHEN IN THE ARM POSITION. // SIGNOFF// REMOVED AND REPLACED FWD AND AFT EMERGENCY BATTERY IN REF WITH PHENOM 300 AMM 33-52- 01, OPS CK GOOD.
GROUND POWER UNIT (GPU) POWERED ON GROUND AND GPU EXTERNAL POWER RECEPTACLE STARTED BURNING AT CONNECTION ON AIRCRAFT AND AIRCRAFT EXTERNAL POWER RECEPTACLE ALSO BURNING. REMOVED AND INSTALLED NEW GROUND POWER RECEPTACLE SUPPORT PART NUMBER 505-06480-403 IN ACCORDANCE WITH EMBRAER PHENOM 300 STRUCTURAL REPAIR MANUAL 51-42-01, PERFORMED REPLACEMENT OF THE AIRCRAFT EXTERNAL GROUND POWER UNIT RECEPTACLE AND INSTALLED A NEW RECEPTACLE PART NUMBER MS3506-1 IN ACCORDANCE WITH EMBRAER PHENOM 300 AMM 24-41-21. REMOVED EXTERNAL POWER WIRE W310 AND REPLACED WITH NEW WIRE PART NUMBER 505-26140-401 IN ACCORDANCE WITH EMBRAER PHENOM 300 AMM 24-41-01. NO OTHER PART AFFECTED. ENERGIZED AIRCRAFT USING EXTERNAL GROUND POWER UNIT IN ACCORDANCE WITH EMBRAER PHENOM AMM 24-41-00. NO OTHER DEFECTS NOTED.
DURING ACCOMPLISHMENT OF EMBRAER SB 505-55-0004 REV 01 (DATED 06/24/2020), WE NOTED THE FOLLOWING MASS BALANCE WEIGHTS BELOW TOLERANCE AT LEFT ELEVATOR: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (16 EACH BELOW MINIMUM OF 84G); HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G). ALL WEIGHTS HAVE BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED. THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11094-615, AS PER SB INSTRUCTIONS. WE ALSO NOTED THE FOLLOWING RIGHT ELEVATOR MASS BALANCE WEIGHTS BELOW TOLERANCE: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (11 EACH BELOW MINIMUM OF 84G); HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G); MASS WEIGHT INBOARD PART NUMBER PE915109-L40 (1 EACH BELOW MINIMUM OF 2809G); MASS WEIGHT OUTBOARD PART NUMBER PE915109-L41 (1 EACH BELOW MINIMUM OF 2049G). ALL WEIGHTS HAVE BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED. THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11094-616, AS PER SB INSTRUCTIONS. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATORâS GMM REQUIREMENTS.
DURING MX EVENT FOUND COMPRESSOR DRIVE MODULE POWER TERMINAL AND ASSOCIATED CONNECTOR HEAT DAMAGED // SIGNOFF // REMOVED AND REPLACED COMPRESSOR DRIVE MODULE, PALLET IAW AMM 21-52-00 OPS CHECKED AND LEAK CHECKED GOOD. REMOVED AND REPLACED RECEIVER DRYER IAW MM CH 21-52-07 PN# 1134275-12 NSN CRIMPED B+ TERMINAL TO WIRE GOING TO THE COMPRESSOR DRIVE MODULE IN REF AMM 20-13-61 NO OTHER DEFECTS NOTED. REMOVED AND REPLACED CONNECTOR P1071 IAW WMM 21-52-50.
ON DEPARTURE AND UPON RETRACTING THE FLAPS FROM FLAPS 1, RECEIVED A FLAPS FAIL CAS MESSAGE. THE FLAP INDICATOR WAS SHOWING AN X. QRH WAS PERFORMED. MOVING THE FLAP HANDLE HAD NO EFFECT. THE FLAP HANDLE WAS PLACED ON THE ZERO POSITION. DURING POST FLIGHT, THE FLAPS WERE FOUND STILL IN THE FLAPS 1 POSITION. SPOILER FAULT WAS ALSO NOTED. FOUND CAS MESSAGE PRESENT. POSITIONED FLAP LEVER FROM 0 TO 1 BACK TO 0. FLAPS FAIL CAS EXTINGUISHED. FLAPS RESET. PERFORMED SEVERAL OPS CHECKS OF FLAPS IAW MM 27-50-00-710-801-A. OPS CHECKED GOOD. CHECKED CONNECTORS AT FCE 1. NO DEFECTS NOTED. PERFORMED SEVERAL MORE OPS CHECKS OF FLAPS. OPS CHECKED GOOD.
BRAKE FAIL CAS MSG ON LANDING ROLL OUT, STILL HAD RT BRAKE WITH NO ANTI-SKID. ODOR NOTICED IN COCKPIT OF PLANE. ACFT WAS TOWED FROM TAXIWAY. TROUBLE SHOT BRAKE FAIL, FOUND RT MLG WST & WOW HARNESS DEFECTIVE. REPLACED RT WOW & WST HARNESS, PN 2317-1146-401, NSN WITH NEW IAW CMM CH 32-11-01. OPERATIONS CHECKED GOOD. REPLACED BRAKE CONTROL UNIT WITH MODIFIED BCU IAW REQUEST OF MFG CONTACT CTR IAW MM CH 32-41-01. OPERATIONS CHECKED GOOD.
AFTER TAKEOFF, NOTICED A CHEMICAL ODOR. NO SMOKE IN CABIN. WENT ON OXYGEN AND RETURNED TO DEPARTURE. ON GROUND, RAN ENGINES INDEPENDENTLY AND NO ODOR DETECTED.
WHEN AVIONICS POWER WAS BROUGHT ON, ARCING SOUNDS WERE HEARD ALONG WITH THE ODOR OF BURNED ELECTRONICS. NO C/B POPPED. RMU 1 SCREEN FLICKERING RAPIDLY. REMOVED INSTRUMENTS AND CB PANEL. FOUND LINT & DEBRIS. CLEANED AS REQUIRED. REMOVED RMU, WILL SUPPLY EXCHANGE UNIT. INSPECTED INSTRUMENT PANEL ITEM. NO EVIDENCE OF ARCING OR SMOKE. INSTALLED CUSTOMER SUPPLIED RMU. OPS CHECK GOOD IAW MM 23-13-00. REINSTALLED REQUIRED CB PANEL AND INSTRUMENT PANEL IAW 24-50-02 OF THE MM.
LEFT MLG INDICATOR LIGHT DID NOT ILLUMINATE WHEN GEAR WAS PUT DOWN. ROTARY TEST: LIGHT OUT, UNLOCK LIGHT EXTINGUISHED. WITH FLAPS DOWN, THROTTLES IDLE, SPEED BELOW 150KTS: NO HORN. GEAR BLOWN WITH EMERGENCY SYSTEM USING CHECKLIST PROCEDURES. RELAMPED LT MLG INDICATOR LIGHT WITH NEW BULB. IAW MM 33-10-00. OPS CHECKED, NO DEFECTS NOTED. JACKED ACFT & RESET AUXILIARY GEAR EXTENSION SYS. ACCOMPLISHED SEVERAL GEAR SWINGS WITH NO DEFECTS NOTED. IAW MM 32-01-00. RESERVICED GEAR/BRAKE BOTTLE IAW MM 12-13-00.
NO AIRSPEED ON CAPTAIN PFD. ABORTED AT 75 KTS.
LT PITOT TUBE WAS OBSTRUCTED BY SOME FOREIGN DEBRIS DURING TAKEOFF ROLL, HAD TO ABORT. NO AIRSPEED ON CAPTAIN PFD. ABORTED AT 75 KTS. REMOVED FWD LT NOSE BAGGAGE COMPARTMENT PANEL. DISCONNECTED PILOT LINE FROM ADC. USED N2 AND BLEW OUT PILOT LINE. NOTED NO FURTHER DEBRIS. CONNECTED LINE. CONNECTED PILOT SYS TEST EQUIPMENT. COMPLIED WITH PILOT SYS OPS AND LEAK CHECKS NOTING NO DISCREPANCIES. INSTALLED BAGGAGE PANEL AND DISCONNECTED PILOT TEST EQUIPMENT. ALL WORK IAW CN 34-11-00 OF THE MM.
RT SEAT BRAKES ARE SPONGY. PERFORMED BRAKE BLEED ON BOTH BRAKES, NO LEAKS NOTED & BRAKES ARE GOOD REF CE560E 32-42-00.
AT APPROXIMATELY 70 KNOTS THE ANTI-SKID INOP LIGHT CAME ON. ABORTED THE TAKEOFF. REMOVED THE LT ANTI-SKID TRANSDUCER WIRE BUNDLE FROM LEFT GEN TO WHEEL WELL CONNECTOR DUE TO OPEN. INSTALLED NEW WIRE BUNDLE IAW CE5650 M/M CH 32-42-00. OPS CHECKED GOOD.
RT PFD FAILURE ATTITUDE AND HEADING FLASH RAPIDLY ATT ANNUNCIATOR ON LT PFD FLASHES. HAPPENS INTERMITTENTLY. AUTOPILOT DISCONNECTS FREQUENTLY WHEN COUPLED TO RT SIDE NR 2 RT PFD DISPLAY WORKS. R & R NR 1 & 2 STATIC INVERTER. OPS CHECK GOOD IAW MM 24-20-04.
LEFT GEAR LIGHT DID NOT ILLUMINATE WITH THE GEAR DOWN CONFIRMED LIGHT INOP WITH ROTARY TEST. CYCLED GEAR 3 TIMES WITH NO CHANGE. VISUALLY CONFIRMED GEAR EXTENDED. FOLLOWED EMERGENCY GER EXTENTION CHECKLIST WITH NO CHANGE. AFTER LANDING CONFIRMED GEAR LOCKED BEFORE TAXI IN TO FBO. JACKED AIRCRAFT AND CYCLED GEAR IAW CESSNA 560 MM 32-01-00. INSTALLED NEW BULB P/N S3368-2 IN LH DOWNLOCK LIGHT. DURING GEAR CYCLES, ALL INDICATIONS NORMAL. DOWNJACKED AIRCRAFT, SERVICED EMERG. GEAR BOTTLE AND HYD. RESERVOIR AS REQUIRED. SAFETIED EMERG. GEAR ARM.
UPON TAXI IN THE LINE PERSONNEL ADVISED US THAT THE RT MAIN GEAR WAS SMOKING. THERE APPEARS TO BE A FILM OF OIL OR GREASE ON THE OUTSIDE AND PORTIONS OF THE INSIDE OF THE TIRE. CLEANED RT MAIN GEAR BRACKET WHEEL ASSY VISUALLY INSP'D FOR LEAKS, EXERCISED BRAKES, SET PARKING BRAKE FOR 1 HR, INSP'D FOR LEAKS, NONE NOTED, CLEANED RH MAIN GEAR WHEEL WELL INSP'D FOR LEAKS, CK'D UPLOCK AND MAIN GEAR ACTUATOR B-NUTS FOR SECURITY, SATISFACTORY AT THIS TIME PER CE 560 M/M CH 32-42-01 & CH 29-11-00
WHILE AIRCRAFT WAS STOPPED AND RT SIDE BRAKE PRESSED POWER LO PRESSURE AND ANTI-SKID ANNUNCIATORS ILLUMINATED. INITIALLY HAD SOME BRAKE PRESSURE. TAXIED CLEAR OF ACTIVE TAXIWAY THEN LOST TOTAL PRESSURE BOTH SIDES NORMAL BRAKES PEDALS WENT TO THE FLOOR SOFT. USED EMER. BRAKES FOR 3 SMALL PULLS TO STOP AIRCRAFT. REMOVED AND REPLACED ANTI-SKID MOTOR RELAY. ALSO FOUND A BROKEN WIRE ON NR2 WHEEL SPEED TRANSDUCER. REPAIRED WIRE, BLED ANTI-SKID HYDRAULICS SYSTEM. TAXI CHECKED GOOD. IAW CE 560 MM 32-42-00 AND CE 560 WIRING MANUAL 20-10-06.
ON SHORT FINAL, ANTI-SKID INOP AND POWER BRAKE LOW PRESS LIGHTS ILLUMINATED. NO BRAKES ON LANDING. LARGE HYD FLUID LEAK NOTICED ON POST FLIGHT. FLUID ON NOSE GEAR & INSIDE NOSE COMPARTMENT. REMOVED AND REPLACED PUMP ASSY, REPLACED FILTER ELEMENT & FILTER CASE BOWL. PERFORMED ANTI SKID BRAKE BLEED IN ACCORDANCE WITH MM 32-42-00. OPS AND LEAK CHECKED GOOD.
ON LANDING PILOT APPLIED BRAKES WITH NO RESPONSE (HARD PEDAL) COPILOT APPLIED BRAKES WITH SAME RESULT. SEVERAL APPLICATIONS WERE MADE. AT 70KIAS BRAKES LOCKED MONENTARILY, ANTI SKID LIGHT ILLUMINATED AND REMAINED ON UNTIL SHUTDOWN. AFTER ILLUMINATION THE BRAKES FUNCTIONED NORMALLY. APPLIED POWER TO A/C. ANTI-SKID ANNUNCIATOR/TEST, OPS CKS GOOD. REMOVED LT & RT HUB CAPS. FOUND LT TRANSDUCER CLIP BROKEN & HUBCAP FULL OF WATER. REMOVED TRANSDUCER & CLEANED ALL WATER. NO DEFECTS NOTED. INSTALLED TRANSDUCER. ANTI-SKID FUNCTION OK, CKS GOOD. FOUND RT CLIP GAP OUT OF TOLERANCE. REMOVED & REPLACED LT & RT CLIPS. RECONFIGURED A/C. BRAKE OP CK GOOD ON ENGINE RUN.
AFTER TAKEOFF, RT MAIN GEAR WOULD NOT RETRACT, FLYING AT APPROX. 200 KTS. THE RT MAIN GEAR LIGHT WAS ON ALONG WITH THE GEAR UNSAFE LIGHT, THE HYDRAULIC LIGHT DID GO OUT. RAN THE EMERGENCY GEAR EXTENSION CHECK LIST AND BLEW THE GEAR DOWN, GOT THREE GREEN LIGHTS AND LANDING WAS NORMAL. ITEM IS UNDER INVESTIGATION.
ON LANDING BRAKES FELT WEAK, DURING TAXI BRAKES FUNCTIONED INTERMITTENTLY UNTIL BRAKES FAILED COMPLETELY, USED EMERGENCY BRAKES TO STOP AIRCRAFT. ITEM IS UNDER INVESTIGATION.
NOTICED HYDRAULIC FLUID LEAKING ON NOSE STRUT. FOUND NOSE GEAR EXTEND HYDRAULIC LINE SEVERELY CHAFED AND LEAKING FLUID. LINE WAS POSITIONED SUCH THAT EVERY TIME THE GEAR WAS RETRACTED THE GEAR CONTACTED THE LINE, THEREBY CAUSING THE CHAFING. IF LEAK IS SERIOUS ENOUGH, HYDRAULIC FLUID COULD BE DEPLETED FROM SYSTEM. SUGGEST INSPECTING ALL HYDRAULIC LINES IN THE NOSE WHEEL WELL AREA FOR IMPROPER ROUTING AND CHAFING.
CONNECTOR FOR OIL TEMPERATURE AT ENGINE MISLABELED, P.93. PER MANUFACTURER, CONNECTOR SHOULD BE LABELED P.87.