N730QS
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 CLIMB AT 1500 FEET AND AFTER SWIRCHING THE BLEEDS FROM APU TO ENGINES, WE SAW SMOKE COMING OUT OF ALL VENTS IN THE COCKPIT AND SMELLED WHAT WE BELIVE IS ENVIRENMENTAL SMOKE. WE DECLARED AN EMERGENCY AND LANDED ABIUT 10 MINUTES LATER. THE TEMPERATURE IN THE COCKPIT KEPT INCREASING BUT THE SMOKE DISSIPATED. REPLACED ACM. OPS CHECK GOOD. IAW CL-350 AMM: 21-52-13
LEFT MLG BRAKE: AFTER NORMAL LANDING AND TAXIING TO CUSTOMS RAMP, CUSTOMS AGENTS NOTICED SMOKE COMING FROM L MAINS. I LOOKED AND ALSO SAW THE SMOKE AS WELL AS FLUID DRIPPING FROM L OUTBOARD BRAKE. AS PRECAUTION, WE DECIDED TO GET TUGGED OVER TO RAMP ONLY TO FIND LEFT OUTBOARD BRAKE IS SEIZED. CORRECTIVE ACTION: RECONNECTED THE HYDRAULIC LINE TO THE BRAKE REF CL350 AMM 32-43-13. OPS CHECK GOOD.
ON THE LOWER FUSELAGE SKIN AT FS 422 & 779 CORROSION WAS FOUND AROUND THE FASTENER HOLES WHERE THE LOWER FUSELAGE TO WING FAIRINGS ATTACH. AFTER REMOVING THE CORROSION AND THE EVALUATION DETERMINED THE SKIN IN THOSE AREAS WAS OUT OF LIMITS. ENGINEERING WAS REQUESTED FOR REPAIR INSTRUCTIONS. AQRD PROVIDED ERO-982224 REV. IR TO FACILITATE TO REPAIR.
DURING CLIMB, THRU 18,000, AN EFIS MISCOMPARE CAS MESSAGE DISPLAYED FOLLOWED BY AN ALT MISCOMPARE BOX. COMPARING 3 SYSTEMS, DTEREMINED THE LT SIDE ADC AT FAULT. ALTITUDE & AIRSPEED WERE BOTH INCORRECT. STOPPED CLIMB & DESCENDED TO FL 200. HAD MANY CASCADING CAS MESSAGES ASSOCIATED WITH A FAILED ADC. AP STAB TRIM FAIL AMBER MACH TRIM FAIL AMBER YAW DAMPER FAIL AMBER SPOILER FAULT CYAN STAB TRIM FAULT CYAN R ENG THRUST FAULT CYAN L ENG THRUST FAULT CYAN REVERTED ADC TO ADC 2 & DIVERTED. REMOVED AND REPLACED #1 ADC IAW CL-350 AMM 34-13-01; OPS CHECKED GOOD.
ON DESCENT AT AROUND 6,000 FT & APPROXIMATELY 250 KTS FLAP FAIL EICAS ILLUMINATED. RAN FLAP FAIL QRC AND DIVERTED TO SWF FOR A LONGER RUNWAY. FLAP FAIL MESSAGE REMAINED ILLUMINATED THROUGH SHUTDOWN. DIAGNOSTIC DATA: POSITION SENSOR FAULT ID# B3-007120. POWERED UP AIRCRAFT. NOTED FLAP FAIL AMBER CAS. INTERROGATED MDC & CONFIRMED BOTH HISTORICAL FAULTS NOTED IN DISCREPANCY. PERFORMED FLAP RESET AND CLEARED CAS. OPERATED FLAPS WITH NO FAULTS NOTED. CONTACTED MCC WHO REQUESTS REPLACEMENT OF LEFT FLAP POSITION SENSOR. REMOVED AND REPLACED LEFT FLAP POSITION SENSOR REF CL-3SOS MM CHAPTER 27·52-17. PERFORMED ELECTRICAL RIG. OPS CHECK GOOD. CLOSED ACCESS.
MAIN DOOR: THE MAIN CABIN DOOR IS VERY DIFFICULT TO CLOSE. YOU NEED TO REALLY PUSH ON IT TO GET IT CLOSED FROM THE EXTERIOR. WHEN CLOSING IT FROM INSIDE IT TAKES A GOOD BIT OF PULLING ON IT TO GET IT CLOSED. PERFORMED A FUNCTIONAL TEST OF THE MED WITH NO DEFECTS NOTED. ALL WORK PERFORMED WITH REFERENCE TO THE CL350 MM 52-11- 00-720-801.
CABIN EMERG LIGHT: THE EMERGENCY LIGHTS UNDER SEAT 4R ARE ON WITH THE EMER LTS SWITCH IN THE ARM AND OFF. IN THE ON POSITION, ALL LIGHTS ARE ON, AS THEY SHOULD BE. PICTURE INCLUDED // SIGNOFF // VERIFIED DISCREPANCY. SWITCHED THE LIGHT FROM SEAT 4R WITH LIGHT FROM SEAT 3R. FAULT DID NOT FOLLOW. SWITCHED BACK AND GAINED ACCESS TO BOTH OF THE EMERGENCY BATTERIES PACKS. BOTH OF THE EMERGENCY BATTERY PACKS DID NOT HAVE A POPPED CB. PULLED BOTH CB'S AND LIGHTS DID NOT GO OFF. PLACED 2 BATTERY PACKS ON ORDER RETURNED AIRCRAFT BACK TO ITS ORGINAL CONDITION. WORK PERFORMED IAW CL-350 SMM 33-50-03 RECIEVED BATTERY PACK REMOVED FWD EMERGENCY LIGHT BATTERY PACK PN BR9767-001 SN C1145 DUE TO INTERNAL FAILURE INSTALLED NEW BATTERY PACK PN BR9767-001 SNC1692. POWERED UP A/C AND CHARGED BATTERY PACK AS REQUIRED PERFORMED OPS CHECKS AND CHECKS GOOD. WORK DONE IAW CL350 SMM 33-50-03 RETURNED A/C BACK TO ORGINAL POSITION
AFTER DEPARTURE AT APPROX 3000" IN CLIMB, RED GEAR NOT DOWN CAS MESSAGE CAME ON ALONG WITH GEAR HORN. BOTH RADAR ALTIMITERS FLUCUATED WITH A RANGE OF RA ALTITUTDES MUTIPLE TIMES, EVENTUALLY THE LT RA SHOWED 0 FOR THE REMAINDER OF THE FLIGHT WHILE THE RIGHT RA READOUT RETURNED TO NORMAL. ALSO ENROUTE INTERMITTENT SP PUSH INOPERATIVE AND EFIS COMPUTER FAIL MESSAGES OCCURED. GEAR NOT DOWN MESSAGE REMAINED ON FOR REMAINDER OF FLIGHT UNTIL THE GEAR WAS LOWERED. VERIFIED DISCREPANCY, R & R NR 1 RADAR ALTIMETER TRANSCEIVER. PERFORMED OPS CHECKS WITH NO DISCREPANCIES NOTED AT THIS TIME. ALL WORK PERFORMED IAW MM 34-41-05.
A/P PITCH TRIM CAUTION LIGHT CAME ON WHILE CLIMBING THROUGH 10-12 THOUSAND FEET. UPON DISENGAGING THE AUTO PILOT, ACFT PITCHED UP SLIGHTLY DUE TO NOSE UP PITCH SETTING, PITCH TRIM ADJUSTED BACK DOWN WITH THE NORMAL TRIM SWITCH AND CAUTION LIGHT WENT OUT. UPON RE-ENGAGING THE AUTOPILOT THE CAUTION LIGHT CAME BACK ON AND NOSE PITCHED UP WITH A RUN-AWAY PITCH UP CONDITION. DISCONNECTED PITCH TRIM WITH EMERGENCY DISCONNECT SWITCH, & LANDED UNEVENTFULLY. REMOVED HORIZONTAL STABILIZER TRIM ACTUATOR AND INSTALLED REPAIRED UNIT IAW CMP 274301. PERFORMED HORIZ. STAB TRIM SYSTEM FUNC. TEST IAW MM 27-40-00. PERFORMED AUTOPILOT FLIGHT DIRECTOR FUNC. TEST IAW G200 CMP 224010.
LANDING GEAR FAILED TO RETRACT.
GEAR FAILED TO RETRACT (CYCLED GEAR PER QRH STILL UNABLE TO RETRACT) (AMBER LT MAIN GEAR INDICATOR TURNED RED - SELECTED DOWN - GOT 3 GREEN IAW QRH). REMOVED AND REPLACED LT MLG ACTUATOR WITH A REPAIRED UNIT. ALL LK AND OPS CK ARE COMPLIED WITH NO OTHER DEFECTS NOTED. ALL WORK DONE IAW MM 32-10-20.
AFTER TAKEOFF, AFTER GEAR LEVER MOVED TO "UP" LT INDICATED AMBER IN TRANSIT LIGHT ON, GEAR WAS CYCLED DOWN HAD 3 GREEN LIGHTS. BROUGHT GEAR UP, LT SIDE MAIN HAD RED GEAR UNDAFE INDICATION, GEAR DOWN W/3 GREEN. BLED LT MLG ACTUATOR IAW MM CH 32-10-00. PERFORMED LANDING GEAR EXTENSION AND RETRACTION IAW MM CH 32-30-00. OPS CHECK GOOD.
AFTER TAKEOFF, AFTER GEAR LEVER MOVED TO "UP" LT INDICATED AMBER IN TRANSIT LIGHT ON,
RUDDER SHAKES INFLIGHT INTERMITTENTLY FROM FL410 DOWN UNTIL AC SLOWED TO 250KTS. FEELS LIKE LIGHT TURBULENCE. THIS WAS THE STRONGEST WE FELT THE SHAKE WHILE DESCENDING. TROUBLESHOT RUDDER TRIM SYS; FOUND FWD LOWER RUDDER TRIM ROD TO HAVE EXCESSIVE PLAY. INSTALLED NEW ROD PN 4A55820111-03 AND BOLT PN NA567040V12 IAW MM 55-40-10.
ON T/O ROLL AT 65KTS EMERGENCY EXIT EICAS CAME ON. T/O REJECTED AND RETURNED TO RAMP. SEVERAL PLACES OF LOOSE HARDWARE IN THE MOUNTING AREA, REINSTALLED SWITCH PLATE AND CHECKED OPERATION SWITCH NOW OPERATING WHEN THE EMERGENCY EXIT HANDLE MOVES APPROXIMATELY .3750 INCH FROM THE STOWED POSTION. REINSTALLED ACCESS PANELS WORK IAW MM 52-20-00.
VERY LOUD DOOR SEAL SQUEAL AFTER TAKEOFF C ALT 200, DIFF 2.3 RATE. REMOVED AND REPLACED PRIMARY DOOR SEAL AND INSPECTED MED VENT DOOR FOR PROPER CLOSING AND STICKING, VENT DOOR WAS STICKING CLEANED SEALING SURFACE AND PERFORMED PRESS CK TO 4.0 PSI NO SQUEAL. ALL WORK PERFORMED IAW G-200 AMM 52-10-13.
AT ABOUT 300' AFTER DEPARTURE SMOKE STARTED ENTERING COCKPIT & CABIN FROM ENVIRONMENTAL SOURCES. SMOKE HAD OILY ODOR & STRONG OILLY ODOR SENSED AROUND LT ENG. CHECKED LT & RT ENGINES FOR OIL LEAKS, NONE NOTED. CHECKED ENGINE BLEED AIR & ECS DUCTS FOR EXCESSIVE OIL , NO EXCESSIVE OIL. FOUND RT ENGINE OIL RESERVOIR OVERSERVICED & SERVICED IT TO PROPER LEVEL. CONDUCTED ENGINE RUNS AT HIGH PWR SETTINGS WITH ECS ON. NO ABNORMAL INDICATIONS AND NO SMOKE IN CABIN OR COCKPIT MX IAW G200 MM TSK 12-17-00-612-801.