N784QS
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
MLG: UPON DEPARTURE WE GOT AN AMBER "GEAR DISAGREE", AND CYAN "PROX SYS FAULT" CAS MESSAGE. RAN THROUGH THE CHECKLIST AND THE CAS MESSAGE DISAPPEARED. CONTINUED FLIGHT WITH GEAR DOWN AND DIVERTED TO KSYR. CORRECTIVE ACTION: FOUND PX05 LEFT MAIN LANDING GEAR UPLOCK OUT OF RIGGING TOLERANCE, ADJUSTED AND RIGGED SWITCH WITHIN TOLERANCE, CHECK GOOD. PERFORMED MULTIPLE LANDING GEAR OPERATIONAL CHECKS, ALL CHECKS GOOD, "PROX SYS FAULT" NO LONGER DISPLAYS. ALL WORK DONE I/A/W CL350S AMM 32-61-09. 32-30-00
IN CLIMB DETENT IN A CLIMB APPROX 27000 FEET R ENGINE EXCEEDANCE CAS ILLUMINATED. WE DID NOT NOTICE A RED ENGINE INSTRUMENT BEFORE WE REDUCED POWER. CONTINUED CLIMB AT A REDUCED POWER SETTING, AND WHILE FNISHING CHECKLIST, N2 GRADUALLY CLIMBED TO 98.1 AND R ENGINE EXCEEDANCE AGAIN ILLUMINATED. N2 BETWEEN LEFT AND RIGHT ENGINE WERE SPLIT BY ABOUT 4-5% AND ITT BY ABOUT 40 DEGREES, BOTH OF WHICH RH ENGINE WAS HIGHER. REMOVED AND REPLACED 5 WORN INLET GUIDE VAIN ARMS. IAW LMM 72-30-10.
BAGGAGE COMPARTMENT ODOR: A NOTICEABLE ELECTRICAL WIRE BURN ODOR IN BAGGAGE/LAV AREA. REMOVED STATIC INVERTER P/N SSC 200 S/N 413 INSTALL STATIC INVERTER P/N SSC 200 S/N 743 IAW BORBARDIER AMM CH. 24-26-01 NEED TO CHECK OPS 06/24/2024 HM JH. RECEIVED AND INSTAUED NEW SPLICE. OPS CHECKED INVERTER SYSTEM, OPS CHECK GOOD AT THIS TIME. RAN SYSTEM FOR SEVERAL HOURS AFTER NEW SPLICE WAS INSTAUED. NO DEFECTS FOUND. PERFORMED WORK IAW BOMBARDIER CL-350 MM CH. 24-26-01 AND AC43.13-1B.
FLAPS FAIL AMBER CAS: FLAPS FAIL IN FLIGHT. EXECUTED NO FLAP LANDING. VERIFIED SQUAWK. SENT MDC AND FCU NVM DOWNLOADS FOR REVIEW. RESET FLAPS AND STILL GOT FLAPS FAIL AMBER CAS. GAINED ACCESS TO FLAP CONTROL UNIT (FCU} - REMOVED EXISTING UNIT, AND REPLACED WITH A CUSTOMER SUPPLIED FCU. COMPLETED ELECTRICAL RIGGING, OPERATIONAL AND FUNCTIONAL CHECKS. ALL CHECKS ARE GOOD. CLOSED ALL ASSOCIATED ACCESS. REF: CL-350 AMM 27-51-05.
AFTER TAKEOFF ON ENGINE BLEEDS, SMOKE STARTED COMING OUT OF THE SIDE AIR VENTS IN THE COCKPIT. SMOKE WAS WHITE & HAD AN OILY ODOR. NO ABNORMAL INDICATIONS OR CASS MESSAGES. ONCE AIR SOURCE KNOB ON AIR CONDITIONING/ BLEED PANEL WAS TURNED TO OFF, THE SMOKE DISSIPATED. OPERATED BLEED AIR SYSTEM & NOTED SMOKE ENTERING CABIN. SHUTDOWN ACFT & INSPD ACM. ACM FOUND SEIZED. ACM R & R IAW MM 21-52-13. INSTALLED REHEATER/CONDENSER & ALL PLUMING IAW MM 21-52·21. R & R TOP OZONE CONVERTER IAW MM 21-52-01. LOWER OZONE CONVERTER IS REPLACED IAW AMM 21-52-01. OPS CHECKED AIR CON SYS IAW AMM 21-52-00. OPS & LEAK CHECKED GOOD.
CUAN "R DC HYD FAIL" CAS MESSAGE DURING THE ENTIRE APPROACH PHASE. CHECKED R DC PUMP ON GROUND, GOT RED HYD PRES LOW MESSAGE. 0 PSI IN RIGHT LINE WITH AMBER HYDRAULIC LINES ON HYDRAULIC SYSTEM PAGE. NO B-3 CODE IN SYSTEM. PER FSR, POWERED UP AIRCRAFT APU AND STARTED LEFT AND RIGHT AIRCRAFT ENGINES PER POH. PERFORMED MULTIPLE OPERATIONAL CHECKS OF THE RT DC PUMP WITH NO DEFECTS NOTED. OPERATED THE FLAPS MULTIPLE TIMES NOTING DC PUMPS OPERATED AS REQUIRED. CONTACTED BEN AND WAS ADVISED THE DC ELECTRIC MOTOR 1S AS THE MOST LIKELY CAUSE OF AN INTERMITTENT R HYO DC PUMP FAIL CAS. PER FSR AND MCC, REMOVED SUSPECTED FAULTY RIGHT HYDRAULIC SYSTEM DC ELECTRIC (BRUSHLESS) MOTOR P/T 1 MLGOA-3 S/N ADI0315 AND INSTALLED. REPAIRED DC ELECTRIC (BRUSHLESS) MOTOR P/N T"1L60A-3 S/N ADL0506 IAW CL350 MM CH. 29-12-05. NOTING HYDRAULIC SYSTEM WAS NOT DISTURBED DURING R&R OF DC ELECTRIC (BRUSHLESS) MOTOR. OPERATIONAL CHECK GOOD, PER MCC AND FSR NO FURTHER ACTION IS REQUIRED.
1 HYDRAULIC PUMP - CYAN L HYD ENGINE PUMP FAIL ILLUMINATED AT FL410. A SHORT PERIOD LATER A CYAN L ENGINE FAULT ILLUMINTED. INITIAL HYDRAULIC SYSTEM SYNOPTICS INDIDATED THAT THE RESERVIOR CONTENTS WERE NORMAL. APPROXIMATELY 12-15 MINUTES LATER THE RESERVIOR CONTENTS DEPLETED AND RESULTED IN A TOTAL LEFT HAND HYDRAULICS SYSTEM FAILURE, (WITH THE EXCEPTION OF BRAKES). SPOILERS FAULT EICAS MESSAGES FOLLOWED AS EXPECTED AS IT RELATES TO THE SYSTEM. *** CORRECTIVE ACTION *** PERFORMED GVI OF THE LEFT ENGINE DRIVEN HYD PUMP, METAL PARTICALS FOUND. TROUBLESHOT AND FOUND LEFT ENGINE HYD PUMP FAILED AND SEALS BLOWN, SHEAR SHAFT INTACT. NO HYDUAULIC FLUID IN NUMBER 1 SYSTEM, EXCESSIVE HYDRAULIC FLUID IN THE ENGINE COWL, STARTER, AND ON ACCESSORY GEARBOX. LARGE QUANTITY OF HYDRAULIC FLUID FOUND IN THE TAIL ACCESS AREA. ADDITIONAL TROUBLESHOOTING FOUND RUPTURED LINE P/N AS119G127K025 1/IPC 29-17-01 ITEM 40. INSTALLED NEW HYDRAULIC LINE, REMOVED AND INSTALLED TESTED LEFT ENGINE HYDRAULIC PUMP. PERFORMED HYD SYSTEM FLUSH AND REPLACED CASE DRAIN FILTERS, PRESSURE FILTER AND RETURN FILTER.
AT FL430, THE MASTER WARNING CHIMED AND A RED CAS RIGHT ENGINE OIL PRESSURE LOW DISPLAYED ON THE EICAS. THE RIGHT ENGINE OIL PRESSURE DIGITS WERE RED READING 25 AND DECREASING. PER THE CHECKLIST WE SHUTDOWN THE ENGINE AND DECLARED AN EMERGENCY. AFTER LANDING, CHECKED THE OIL LEVEL AND CAP AND BOTH WERE NORMAL. A SMALL AMOUNT OF OIL WAS NOTICEABLE ON THE BOTTOM OF THE COWLING. REPLACED RT ENGINE OIL PUMP IAW CMM MM 79-20-04. OPS CHECKED GOOD.