N739QS
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
UPON BRINGING THE GEAR UP ON TAKEOFF, WE GOT A GEAR DISAGREE AMBER CAS MESSAGE. LEFT MAIN GEAR STAYED DOWN. NOSE AND RIGHT MAIN GEAR WENT UP. ACCOMPLISHED THE GEAR DISAGREE QRH. R & R LT STAY ACTUATOR IAW AMM 32-32-07. R &R LT BRACE ATTACH PIN IAW AMM 32-32-08. INSTALLED MODIFIED LT SIDE STAY ACTUATOR IAW AMM 32-32-07. BLED LT & RT HYD SYS IAW AMM 29-10-00. CW OPS & FUNCTIONAL TEST OF EXTENSION & RETRATCTION IAW AMM 32-30-00. OPS & FUNCTIONAL TESTED GOOD. CW OPS TEST OF MLG EMERGENCY EXTENSION IAW AMM 32-34-00. OPS CHKD GOOD.
DURING DESCENT THROUGH 9000 FEET, BOTH PILOTS NOTICED STRONG, EXHAUST SMELL IN THE COCKPIT. ENVIRONMENTAL WERE TRANSFERRED TO THE APU, WHICH MINIMIZED THE SMELL MOMENTARILY. THE SMELL WAS CLOSER TO EXHAUST, NOT DEICING FLUID, NOT ACRID, OR ELECTRICAL. CORRECTIVE ACTION: REMOVED INTERNALLY LEAKING APU P/N 3800774-2 S/N P-847 AND INSTALLED CUSTOMER SUPPLIED INSPECTED APU P/N 3800774-2 S/N P-803. PERFORMED GOOD OPS AND LEAK CHECK. WORK PERFORMED REF CL-350 AMM 49-11-00 AND 49-11-01
RIGHT HYD RESERVOIR DUMPED ALL FLUID TO 0% AT FL430. CYAN FLAPS RATE LOW AND R HYD ENG PUMP FAIL ILLUMINATED. AMBER R HYD LOW AND SPILER FAULT ILLUMINATED WHEN FLAPS EXTENDED VIA ALTN FLAPS. POST FLIGHT SHOWED HYD FLUID DRIPPING FROM BOTH R ENGINE LOWER WEEP HOLES CORRECTION ACTION: REPLACED HYDRAULIC PUMP. IAW CL-350 AMM 05-51-29 AND AMM 29-12-01 OPS CHECK GOOD.
CORROSION WAS FOUND ON THE LOWER FUSELAGE SKIN NEAR FS 779 NEAR STR 22L & 23L, NOMINAL THICKNESS 0.060 IN, MINIMUM 0.035 IN. MATERIAL TYPE 2024-T42 PER AMS-QQ-A-250''5.
MAIN DOOR: MAIN CABIN DOOR WILL NOT OPEN. DOOR HANDLE WILL COME OUT ABOUT HALF WAY BUT THE DOOR WILL NOT RELEASE. CORRECTIVE ACTION: MED CURTAIN MOVED OUT OF THE WAY. OPS CHECK GOOD. IAW CL350 AMM 52-11-00.
ON LANDING, RIGHT BRAKE FELT SPONGEE. RIGHT OUTBOARD BRAKE SMOKING AFTER LANDING. APPEARS TO BE FLUID ON THE INBOARD SIDE OF RIGHT OUTBAORD TIRE. ##4 BRAKE WTL. INSTALLED OVERHAULED #4 RIGHT MAIN BRAKE ASSEMBLY. IAW MM 32-43-13-400-801. PERFORMED BRAKE BLEEDING PROCEDURE IA W CL 350 MM 32-43-00-870-802. OPS AND LEAK CHECKS GOOD.
OVERWEIGHT LANDING: LANDED OVERWEIGHT DUE TO EMERGENCY AND ENGINE FAILURE. PLENTY OF RUNWAY AND GENTLE ON BRAKES. BASED ON THE AMM TASK 05-51-01-210-801 STEP 1.C(3)(A) AND THE INFORMATION PROVIDED FOR THE EVENT (AIRCRAFT LANDING WEIGHT AND RATE OF DESCENT) IT WAS DETERMINED THE LANDING FALLS WITHIN THE *OVERWEIGHT LANDING* ACCEPTABLE RANGE IN REFERENCE TO FIG 601, THEREFORE IT IS NOT NECESSARY TO PERFORM THE AMM TASK 05-51-01-210-801 STEPS 1.D AND 1.E
AT ROTATION, RED CAS & MASTER WARNING. ENG ROLLED BACK, CAME BACK UP, 2ND IDENTICAL CAS FOLLOWED BY ROLL BACK AGAIN. ENG DID NOT HAVE POWER CONTROL FOR ROUGHLY 1 MIN. REMOVED ENG SN: PL36679 DUE TO ITI OVER TEMP OF L 197 DEGREES. INSTALLED REPAIRED ENG SN: PL36250. SERVICED ENG OIL SYS & ATS. COMPLIED WITH VISUAL INSPECT OF REAR ENG MOUNT STRUT SEALS. COMPLIED WITH DETAILED INSPECT OF ENG MOUNT POINTS. COMPLIED WITH WET MOTOR, DRY MOTOR, ENGINE OPS, LEAK CHECK POWER ASSURANCE RUN, EEC INITIALIZATION & THRUST REVERSER ACTIVATION. NO DISCREPANCIES. WORK IN REF TO LMM AS907-2-1.A, 72-05-22, 05-20-00, 72-00-00 REV. 12 & AMM REV. 40, 71-00-00 & OTHER DATA & METHODS ACCEPTABLE TO THE ADMINISTRATOR.
RIGHT HYDRAULIC TEMP HI YELLOW CAS CAME INTO VIEW WHILE IN DESCENT INTO KAUS. RIGHT HYDRAULIC TEMP READ 100 DEGREES CELSIUS PER HYDRAULIC SCHEMATIC DISPLAY. TEMP WENT DOWN TO 70 CELSIUS AFTE RH HYD SOV WAS CLOSED AS PER THE QRH. RAN BOTH ENGINES AND HYD PUMPS FOR 15 MIN. R/H WAS 18 DEG HOTTER. R&R R/H HEAT EXCHANGER BYPASS VALVE.
COCKPIT ODOR: APPROX 15 MIN FROM DESTINATION BEGAN TO SMELL BURRING ODOR. NO VISIBLE SMOKE. APU WAS OFF ENGINE BLEEDS ON. ODOR REMAINED FOR DURATION OFF FLIGHT. WE LANDED WITH APU OFF, DURING TAXI IN STARTED APU AND TRANSFERRED BLEEDS. WE FELT THE AIR FROM THE BLEEDS WAS ABNORMALLY HOT AND CHOSE TO SHUT APU OFF AND TRANSFER BLEEDS BACK ON. APROX 1 MIN LATER AS TAXING INTO BLOCKS WE GOT AN AMBER PACK TEMP HIGH MESSAGE. SHUT DOWN ENGINES AND SECURED AIRCRAFT.
CYAN FIRE SYSTEM FAULT MESSAGE DISPLAYED ON EICAS FOR MOST OF THE FLIGHT. RESEARCHED FIRE SYSTEM AND RESEARCHED LT ENGINE FIRE LOOP B B3-008146 ON SAMRTFIX. GAINED ACCESS TO FIREX BOX, DISCONNECTED A91P2, AND PERFORMED A CONTINUITY CHECK OF PINS 10 AND 11. FOUND CONTINUITY CHECK TO BE GOOD. CYCLES CIRCUIT BREAKERS CB2-A11 AND CB6-A4. CHECKED PINS, CLEANED CONNECTOR, AND RE-SECURED CONNECTOR, IAW CL-350 AMM 26-11-01-04. POWERED UP AIRCRAFT, CHECKED FOR CURRENT FAULTS AND NO FAULTS FOUND. PERFORMED MDC DOWNLOAD AND PERFORMED AN OPERATIONAL TEST OF THE FIRE DETECTION AND EXTINGUISHING [FIREX] SYSTEM, IAW CL-350 AMM 12-11-00-05 SEVERAL TIMES, AND THEN WAS FOUND SATISFACTORY. PREPPED THE AIRCRAFT AND PERFORMED TWO NORMAL STARTS WITH BOTH ENGINES, IAW CL-350 AMM 71-00-00-00 AND NO FAULTS OR CAS MESSAGES APPEARED. CONTACTED NJA MCC AND ADVISED THEM THAT WE COULD NOT DUPLICATE THE DISCREPANCY. NO HISTORY WAS FOUND AND NJA MCC ELECTS TO HAVE THE AIRCRAFT RELEASED.
AT FL320 AND CLIMBING THE AMBER EMERGENCY EXIT CAS LIGHT ILLUMINATED. AFTER DESCENDING BELOW FL280 THE LIGHT WENT OUT. REMOVED & REPLACED EMERGENCY EXIT DOOR PROX SWITCH IAW CL-350 M/M 52-71-21. OPS CHK GOOD.
WHEN RETRACTING GEAR AFTER NORMAL TAKEOFF, NOSE WHEEL WOBBLES AND CAUSES A VIBRATION ON NOSE OF ACFT FOR 10-12 SECONDS.
WHEN BRAKES ARE APPLIED DURING TAXI THERE IS A INTERMITTENT LOUD BANG IN THE NOSE OF THE ACFT WITH THE BRAKES GRABBING. BLED ALL 4 BRAKES AND TAXI CHECKED ACFT, NO DISCREPANCIES NOTED. SERVICED RT HYD RESERVOIR WITH FLUID AFTER BRAKE BLEED. ALL WORK DONE IAW CH 32-40-20 AND 12-15-00 OF THE MM.
IMMEDIATELY AFTER TAKEOFF POWER SET WE GOT THE RED DITCH LIGHT THE YELLOW AUTO PRESS FAULT LIGHT AND THE FOLLOWING EICAS MESSAGES CABIN ALT HIGH AUTO PRESSURE.
IMMEDIATELY AFTER TAKEOFF, POWER SET, WE GOT THE RED DITCH LIGHT THE YELLOW AUTO PRESS FAULT LIGHT AND THE FOLLOWING EICAS MESSAGES CABIN ALT HIGH AUTO PRESS R FADEC MINOR PRESS MONITOR ADDITIONALLY THE CABIN OXYGEN MASK DEPLOYED. INTERAGATED MDC AND FOUND CPC CHANNEL A AND B FAILURE. REMOVED FAULTY CPC AND INSTALLED A REPAIRED UNIT. PERFORMED OPS TEST WITH NO FAULTS NOTED IAW MM 21-30-00 AND 21-30-07 (VERIFY MODE, MANUAL MODE TEST, AUTO PRESSURE TAKEOFF MODE).