N415QS
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
FLOOR EMERG EXIT LIGHT: ENTIRE BANK OF RED EMERGENCY LIGHTS AT SEAT 12 ARE INOP. UPON INITIAL POWER UP, THEY ALL BLINK ON AND GO OUT. // SIGNOFF// OPS CHECKED THE LIGHTS WITH NO DEFECTS NOTED. WORK DONE IN REF G450 AMM 33-50-00.
JUST PRIOR TO TOP OF DESCENT, CAS MESSAGES RECEIVED: AMBER "FLAPS FAILED", BLUE "STABILIZER SYNCING". BEFORE LANDING, THE USE OF FLAPS WAS UNSUCCESSFUL. LANDED ZERO FLAPS. ACCESSED CMC AND INTERROGATED CMC, RECORDED FAULTS. ATTEMPT TO CLEAR FLAPS FAIL CAS MESSAGE BUT UNABLE. POWERED MULTIPLE POWER CYCLES TO NO CHANGE. PREPPED FOR ENGINE RUNS. RAN ENGINES IN ATTEMPTS TO CLEAR FLAP FAIL BUT UNABLE.CONNECTED GPU AND INTERROGATED CMC AND PERFORMED FIM. THE FIM POINTS TO INTERNAL FAILURE OF FSECU. FORWARDED FAULTS TO MCC AND ADVISED FIM POINTS TO FSECU. RETRIEVED FSECU AND VERIFIED PAPERWORK. REMOVED OLD FSECU PN 1159SCC612-17 SN 014, DUE TO INTERNAL FAILURE. INSTALLED INSPECTED FSECU PN 1159SCC612-17 SN 107, IAW G450 AMM 27-51-00. PERFORMED AUTO RIG, IAW G450 MM 27-50-00. SERVICED AND BLED HYDRAULICS AS REQUIRED. REMOVED HYDRAULIC POWER CART. CLOSED UP ACCESS. REQUESTED AIRCRAFT TO BE PULLED FROM H4. PREPPED FOR ENGINE RUNS. PERFORMED ENGINE RUNS AND CYCLED FLAPS. SYSTEMS AND OPS CHECKS GOOD.AMM 27-51-00. PERFORMED AUTO RIG IAW G450 X MM 27-50-00.
FOUND VACUUM WASTE TUBE CLAMP TO BE CONTACTING THE UPPER WING PLANK AT FS 355 DURING COMPLIANCE WITH CUSTOMER BULLETIN 206. INSPECTED AREA AND FOUND ONLY PRIMER WAS RUBBED OFF. CLEANED, ALODINED AND PRIMED AREA, PER GULFSTREAM W/O.
***ENTERING FOR HISTORICAL DATA*** DURING OPERATIONAL CHECK FLIGHT AT 39500', MACH .85 WITH SPED BRAKES DEPLOYED, AILERON TRIM STUCK SOLID AND COULD NOT BE MOVED FOR REST OF FLIGHT. AFTER ENGINE SHUTDOWN, TRIM COULD BE MOVED BUT FELT STIFF.///SIGN-OFF///INSPECTED AILERON TRIM WHEEL , TRIM TAB ACTUATOR AND CABLE RUN FROM PEDESTAL TO AILERON TRIM TAB WITH NO DEFECTS NOTED. PERFORMED AILERON TRIM TAB CABLE TENSION CHECK AND FOUND BOTH AILERON TRIM TAB CABLES TO BE OUT OF LIMITS (28 LBS). RE-TENSIONED AILERON TRIM TAB CABLES TO 42 LBS +/- 10%. AT 50 DEG. F (SUBTRACTED 1.5 POUNDS FOR EVERY 10 DEG. BELOW 70 DEG. F) IN ACCORDANCE WITH G450 AMM CH. 27-12-07. TENSIOMETER # 567269 CAL. DUE: 02/20. REMOVED AND REPLACED AILERON TRIM TAB ACTUATOR PER ITEM 11.5 CMP 271002 AND PERFORMED AILERON TRIM SYSTEM RIGGING CMP 271204 ITEM 11.3 WITH NO DEFECTS NOTED.
BRAKES FELT SMOOTH BUT SPONGY ON LANDING. TAXIED AIRCRAFT AND VERIFIED DISCREPANCY. EXTENSIVELY BLED AIR FROM BRAKE SYSTEM CHARGE. PERFORMED ANOTHER TAXI CHECK WITH SATISFACTORY RESULTS. WORK DONE IN REFERENCE TO AMM 32-41-00. OPS CHECK GOOD.
APU VIBRATED VIOLENTLY AFTER 15 MINUTES OF OPERATION AFTER ENG SHUTDOWN. APU AUTOSHUTDOWN. LARGE QTY OF SMOKE & SOME FLAMES VISIBLE FROM INTAKE. FIRE BOTTLE DISCHARGED. REMOVED AND REPLACED THE APU IAW G-450 MM 49-00-00. OPS AND LEAK CHECKED GOOD.
AFTER TAKEOFF FUEL LEAK OUT OF RT WING OTBD LOWER SIDE LOST 800 LBS FUEL IN ABOUT 4 MINUTES. REMOVED RT WING TANK ACCESS PANEL G21TB-17. AFTER ACCESSING TANK FOUND BOTH FORWARD AND AFT VENT FLOATS STUCK IN THE OPEN POSITION. REMOVED FORWARD AND AFT VENT FLOAT/NON-RELIEVING VALVES P/N 16F123 NSN. INSTALLED A NEW FORWARD VENT FLOAT P/N 12F123/NSN. INSTALLED A NEW AFT VENT FLOAT P/N 16F123. FORWARD AND AFT VENT FLOATS INSTALLED WITH NEW GASKETS 1 EA. GA215-160 AND NEW WASHERS 4EA NAS1149D0316H SECURED WITH PREVIOUSLY REMOVED SERVICEABLE BOLTS 4 EA. INSTALLED RT WING TANK ACCESS DNL 621TB-17. LEAK CHECK GOOD. ALL WORK DONE IAW M/M 28-15-01, 28-10-00, AND 57-01-01. UPDATED CMP CODE 281510 F. FWD VENT FLOAT/NON-RELIEFING VALVE. AND 281512 R. AFT VENT FLOAT NON-RELIEFING VALVE.
UPON BRAKE APPLICATION, NO BRAKING UNTIL TOP OF PEDALS ARE DEPRESSED APPROX 2.5", THEN SUDDENLY 500LBS OF PRESSURE, BRAKES GRAB SUDDENLY. PERFORMED BRAKE BLEEDING PROCDURES WITH LT HYD SYS PRESSURE. NOTED AIR PRESENT WHILE BLEEDING BRAKES. ACCOMPLISHED BRAKE BLEEDS UNTIL AERATION WAS NO LONGER PRESENT. NOTED NO DEFECTS POST BLEEDING ACCOMPLISHMENT, REF MM 32-44-00.
STAB FAIL MESSAGE AND WOULD NOT MOVE.