N217QS
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
EXTERIOR WINDOW EMERGENCY EXTT LAMP WILL NOT ILLUMINATE.SINGLE LAMP IS AFT OF THE EMER WINDOW EXIT
MAIN CABIN DOOR VERY HARD TO CLOSE BY HAND AND DOOR DROPS FAST WHEN OPENING VERY HEAVY DOOR. NEEDS ADJUSTMENT PERFORMED ADJUSTEMENT OF THE MED COUNTERBALANCES IAW CL-650 AMM 52-11-31 PERFORMED FUNCTIONAL CHECK OF THE MED COUNTER BALANCES IAW CL-650 AMM 52-11-31 FUNCTIONAL CHECK GOOD
DURING DESCENT PASSING FL360 RED MASTER WARNING AND RED CAS DIFF PRESS ILLUMINATED. DIFF PRESS WAS 9.1 AND WENT AS HIGH AS 9.7. QRH USED AND FL270 DIFF PRESS WENT FROM RED TO GREEN. APU BLEED NOT TRANSFERRED UNTIL ON THE GROUND. CORRECTIVE ACTION: REPLACED CABIN PRESSURIZATION CONTROLLER IAW CL-650 AMM 21-31-13 OPS CHECK GOOD, LEAK CHECK GOOD
DIFF PRESS RED CAS: DURING DESCENT PASSING FL360 RED MASTER WARNING AND RED CAS DIFF PRESS ILLUMINATED. DIFF PRESS WAS 9.1 AND WENT AS HIGH AS 9.7. QRH USED AND FL270 DIFF PRESS WENT FROM RED TO GREEN. APU BLEED NOT TRANSFERRED UNTIL ON THE GROUND.
MAIN DOOR HANDLE: INSIDE DOOR HANDLE DIFFICULT TO LIFT UP TO UNLOCK. CORRECTIVE ACTION; PERFORMED ADJUSMENT TO DOOR HANDEL LOAD AJUSTMENT BOLT ON INTERNAL HANDEL. PERFORMED OPS CHECKS AND VERIFIED THAT DOOR HANDEL MECHANISM WAS RIGGED CORRECT. OPS CHECKS GOOD AT THIS TIME. WORK PERFORMED IN REF TO CL-650 AMM 52-11-00.
MAIN DOOR: MAIN PASSENGER DOOR HANDLE POPS OUT NORMALLY AND VENT DOOR WORKS, BUT MAIN DOOR HANDLE WILL NOT TURN. CAN NOT OPEN DOOR. CORRECTIVE ACTION: REPLACED ROLLER. ADJUSTED TENSION ON CAM. OPS CHECK GOOD. IAW CL-650 AMM 52-10-00.
RIGHT ENGINE ENGINE INLET: POSSIBLE SMALL BIRD INGESTION ON THE RIGHT ENGINE. CORRECTIVE ACTION: ENGINE INSPECTED. NO DAMAGE OR FOD INGESTED. IAW CL-650 AMM 05-51-20-210-801
ON TAKEOFF & CLIMB OUT CABIN WOULD NOT PRESSURIZE. LEVELED 9000 FT & RAN CHKLST. COULD NOT PRESSURIZE. RETURNED TO LAND. NOISE ON CLIMB OUT CONSISTANT WITH DOOR SEAL. ON POSTFLT FOUND GROUND WIRE DISCONECTED. ACCOMPLISHED OPS TEST OF PRESSURE CONTROL SYS IAW AMM 21-31-00-710·801 & IN MANUAL MODE IAW AMM 21·31· 00-710·802, ALL CHECKS GOOD EXCEPT NOTICED MED SEAL HISSING TOWARDS FWD UPPER EDGE OF DOOR FRAME. CLEANED SEAL & CHKD WITH SAME RESULTS. REMOVED DOOR SEAL, DOOR GAS SPRINGS CABLES, DOOR ACTUATOR CABLE, HANDRAIL OPERATING RODS & GROUND WIRE. INSTALLED NEW SEAL, DOOR GAS SPRINGS CABLES, MED ACTUATOR CABLE, HANDRAIL OPERATING RODS & GROUND WIRE IAW AMM 52-11-28. OPS TESTED GOOD IAW AMM 52-11-00.
ACFT HAD A VERY MUSTY ODOR. USING APU AIR, GOOD FLOW FROM GASPERS. IN FLT WHEN USING ENG AIR, THERE IS VERY LITTLE TO NO FLOW FROM GASPERS. INSPECTED WATER SEPARATORS. REMOVED LT WATER SEPARATOR FOR INSPECTION & REPLACEMENT OF WATER COALESCER BAG IAW MM 21-51-13. REMOVED RT WATER SEPARATOR FOR INSPECTION & REPLACEMENT OF THE WATER COALESCER BAG IAW MM21-51-13. WHILE PERFORMING INSPS OF WATER SEPARATORS, NOTED DUCT FOR EMERGENCY RAM AIR SHUTOFF VALVE BROKEN & NO LONGER CONNECTED TO VALVE, DISASSEMBLED LT WATER SEPARATOR & REMOVED FAULTY LT COALESCER BAG & INSTALLED NEW COALESCER BAG IAW MM 21-51-13. DISASSEMBLED RT WATER SEPARATOR & REMOVED FAULTY RT COALESCER BAG & INSTALLED NEW COALESCER BAG IAW MM 21-51-13. REMOVED FAULTY RAM AIR DUCT ASSY, INSTALLED NEW DUCT IAW MM 21-52-01. STARTED APU IAW AFM. LEAK CHECK IAW MM 21-51-00, NO DEFECTS. STARTED LT & RT ENGS IAW AFM & VERIFIED COCKPIT & CABIN ARE GETTING SUFFICIENT FLOW WITH NO ODOR. ORIGINAL SUBMISSION DATE: 12/26/2023.
AFTER TAKEOFF, AIRCRAFT FAILED TO PRESSURIZE. NOTICED ISSUE AT APPROX 7500¿. CABIN WAS EQUAL TO AIRCRAFT ALTITUDE. LEVELED AIRCRAFT AT 10,000' AND VERIFIED BLEEDS SET AND PACKS ON. WE CONTINUED TO RUN CABIN ALT CHECKLIST. UNABLE TO PRESSURIZE IN AUTO OR MANUAL MODE PER THE CHECKLIST. LOUD WIND NOISE FROM MAIN CABIN DOOR. NO DOOR LIGHTS WERE ILLUMINATED. CHECKED MAIN CABIN DOOR AND ALL GREEN FLAGS IN POSITION. OPTED TO PULL CABIN DOOR T HANDLE TO VERIFY VENT CLOSED. WIND NOISE REDUCED WHILE HANDLE WAS PULLED BUT CAME BACK WHEN HANDLE WAS STOWED. AIRCRAFT DID NOT ATTEMPT TO PRESSURIZE. WE DESCENDED TO 8000' AND WERE REQUIRED TO HOLD TO BURN FUEL OFF. SHORTLY AFTER LEVEL OFF AT 8000¿ DOOR NOISE REDUCED AND IT APPEARED THAT CABIN BEGAN TO PRESSURIZE. DELTA PRESSURE INCREASED FROM 0 TO 3.2 AND CABIN ALTITUDE DROPPED TO 1000' AND REMAINED THERE FOR REMAINDER OF FLIGHT. WE DID NOT CLIMB HIGHER THAN 8000' FOR REMAINDER OF FLIGHT. DOOR NOISE SEEMED HIGHER THAN NORMAL DURING LANDING. OP TEST OF THE PRESSURIZATION CONTROL SYSTEM AUTO AND MANUAL MODE C/O IAW 21-31-00 DOOR MECHANISM INSPECTED NO FAULTS WAS FOUND PRESSURE RUN C/O WE CANNOT DUPLICATE THE FAULT. CARRIED OUT OP TEST OF PRESSURIZATION CONTROL SYS (AUTO AND MANUAL) MODES. OP TEST OF THE PRESSURIZATION CONTROL SYS (AUTO AND MANUAL MODES) CARRIED OUT WITH NO FAULTS IAW AMM 21-31-00-710-801/802 REV 30. CARRY OUT A PRESSURIZATION LEAK CHECK AIRCRAFT PRESSURIZATION IAW 21-30-00-790-801 REV 30 SMALL LEAK FOUND DOOR PRESSURE VALVE SEAL CLEANED AND LOWER BONDING LEAD RELOCATED CARRY OUT A PRESSURIZATION LEAK TEST PRESSURIZATION LEAK TEST CARRIED OUT IAW AMM 21-31-00-740-801 REV 30. ORIGINAL SUBMISSION DATE: 9/21/2023
RIGHT ENGINE ENGINE VIBRATION INDICATION: DESCENDING OUT OF 35000 THE RIGHT N2 VIB MESSAGE ILLUMINATED ON THE RIGHT N2 DIAL FOR ABOUT 10 SECONDS. DID NOT SEE ANY OTHER INDICATIONS ALTHOUGH IT DID SOUND LIKE A VERY SLIGHT CHANGE IN ENGINE HUM OCCURRED. THE VIB INDICATION WENT OUT BUT CAME ON AGAIN FOR A FEW SECONDS THROUGH ABOUT 32000 FEET. // SIGNOFF// REMOVE ACCELEROMETER LEADS AND CHECK FOR DAMAGE. CHECK ACCEROLOMETER IAW CH650 CMM 77-30-10 AND GE CF34 SM SE1-780 F1 38. LEADS REMOVED AND FOUND NO DAMAGE. FOUND EBRIS INSIDE THREADED HOLE OF MATING SURFACE OF ACCELEROMETER AND FLUSHED WITH ALCOGOL ACCELEROMETER FAILED CAPACITANCE TEST IAW CH650 CMM 77-30-10 (C)(2)(B) AT 1700 PF MAX LIMIT OF 1550 PF CHECK FAN BLADES FOR FOD DAMAGE AND GREEDOM OF MOVEMENT IAW GE CF34 SM SE1-780 REF GECF34 HMM SE1-782 72-21-00. INSPECTED FAN BLADES FOR FREEDOM OF MOVEMENT ALL BLADES IN SERVICEABLE AND OPS CONDITION NO DAMAGE NOTED. IAW GE CF34 HMM SE1-792 72-21-00 PERFORM FUNCTIONAL CHECK OF SIGNAL CONDITIONER IAW GE CF34 SM SE1-780 F1 38. PERFORMED FUNCTIONAL TEST OF SIGNAL CONDITIONER VIA ENGINE VIBRATION MONITORING SYSTEM IAW CH650 AMM TASK 77-31-00-740-801 NO DEFECTS NOTED. PERFORM INSPECTION OF MAGNETIC CHIP DETECTOR AND OIL FILTER IAW GE CF34 SM SE1-780 REF GE CF34 SM SE1-780 MP34. CHIP DETECTOR HAD EVIDENCE OF UNUSUAL WEAR PATTERNS ON THE MAGNET BUT WAS DETERMINED TO BE ACCEPTABLE WEAR IAW CF34 SM SE1-780 FIGURE 604 MASTER CHIP DETECTOR INDICATOR DID NOT ILLUMINATE, SO OIL FILTER WASNT REMOVED. BORESCOPE REQUIRED FOR COMPRESSOR SECTION AND HPT IAW GE CF34BJ SMM SE1-780 H 38. RH ENGINE COMPRESSOR SECTION AND HPT BORESCOPE C/W IAW CF34BJ SERVICE MANUAL SEI-780 SM 72-00-00 NO DEFECTS NOTED TEST EQUIPMENT USED FOR ITEM 1: BASDAL2581 18MAR24 BASDAL5279 22MAY24 RH ENGINE BORESCOPE PLUGS 533 534 535 537 540 541 545 547 AND 549 REMOVED IAW CF34BJ SERVICE MANUAL SEI 780 SM 72-00-00. OK TO INSTALL INSTALLED RH ENGINE BORESCOPE PLUGS 533 534 535 537 540 541 545 547 AND 549 IAW CF CF34BJ SERVICE MANUAL SEI 780 SM 72-00-00 TORQUE WRENCH BASDAL6023 CAL DATE 5/22/24 INSPECT RH FWD AND AFT ENGINE MOUNTS IAW SE1-780 FI 38 REMOVED PANEL PYLON 422CT (SEE ITEM 18 FOR INSTALL) MANUALLY RETRACTED THRUST REVERSERS IAW CL650 AMM TASK 78-30-00-910-802 PERFORMED VISUAL INSPECTION OF FORWARD MOUNT IAW CE CF34 SM SE1-780 REF CH 650 AMM TASK 91-21-01-220-801 (D)(1) TO (D)(4) NO DEFECTS NOTED. PERFORMED VISUAL INSPECTION OF REAR ENGINE MOUNT IAW GECF34 SM SE1-780 FI38 REF CH650 AMM TASK 71-22-01-220-802 NO DAMAGE FOUND. RH ENG MASTER CHIP DETECTOR REQUIRES LEAK CHECK IAW GE CF34 SM SE1-780 PARA G. LEAK CHECK OF R/H ENGINE MASTER CHIP DETECTOR GOOD REF GE CF34 SM SEI-780 RH G LEAK CHECK GOOD REF ITEM 1: REMOVED ACCELEROMETER PN: 600-59131-1 SN: 21861 FOR TEST IAW CH650 AMM TASK 77-31-01-000-801. OK TO INSTALL INSTALLED NEW ACCELEROMETER IAW CH650 AMM TASK 77-31-01-400-801 PN 600-59131-1 SN: 22137 BASDAL162 27-FEB-24 BASDAL6541 22MAY24 PYLON ACCESS PANEL 422CT DOCUMENTED REMOVED UNDER CORRECTIVE ACTION STATEMENT IN ITEM #9 REQUIRES INSTALL REF CL650 AMM 54-60-01-000-801. OK TO INSTALL. INSTALLED PYLON ACCESS PANEL 422CT IAW CL650 AMM 54-60-01-400-801 REMOVED RH MASTER CHIP DETECTOR PN: 4920750CN5071T94P03. OK TO INSTALL. INSTALLED ORIGINAL MASTER CHIP DETECTOR IAW GE CF34 SM SE1-780 MP34 BASDAL6030 27-MAR-24 RUN ENGINES REQUIRE FOR SENSOR REF CL650 MM CH 77-31-01-400-801. RAN ENGINES AND VERIFIED VIB SENSOR OPERATING NORMALLY AND NO MESSAGES BUSTED AT THIS TIME REF CL650 MM CH 77-31-01-400-801 REF ITEM 9 REMOVED PANEL 422AT IAW CH650 AMM TASK 54-60-01-000-801. TRANSFERED TO W/O 260163 SVO # 12849814 CTRL 9001. ORIGINAL SUBMISSION DATE: 6/14/2023
EMERG EXIT SIGN/LIGHT: EMERGENCY EXIT SIGN LIGHT UNDER DIVAN IS INOP. // SIGNOFF// POWERED ON AIRCRAFT, DURING TROUBLESHOOTING OF AIRCRAFT GAINED ACCESS TO SIGN WIRING, UPON WIRING CHECKS AND VOLTAGE CHECKS FOUND PINS GOING TO LIGHT TO BE LOOSE AND INTERUPTION OF CONNECTION WAS SUBSEQUENTLY OCCURING, PROPERLY REINSTALLED CONNECTOR INTO MOLEX CONNECTOR AND OPS CHECKED GOOD. NO FURTHER DEFECTS NOTED. ALL WORK DONE I/A/W CL650 AMM 33-51·00
MAIN DOOR: MAIN CABIN DOOR WILL NOT LOCK SHUT. FROM THE INSIDE WHEN YOU PULL THE STOW HANDLE THE INDICATOR KEEPS POPPING RED AND WHEN YOU TRY TO SHUT IT FROM THE OUTSIDE THE HANDLE KEEPS POPPING OUT. INSPECTED THE OLITER DOOR HANDLE AND FOUND THE SCREWS FOR THE LOCK BACKED OUT AND HITTING THE STRUCTURE FOR THE DOOR HANDLE. THIS WAS PREVENTING THE HANDLE FROM BEING FULLY RECESSED. TIGHTENED THE SCREWS IAW CL650 SPM 20-21-00. OPS CHECK OF THE OUTER HANDLE STOW MECHANISM IS SATISFACTORY IAW CL650 AMM 52·11-07.
ONE OF THE CABLES BECAME LOOSE ON THE AFT SIDE OF THE MAIN CABIN ENTRY DOOR. THE CREW WAS UNABLE TO OPEN THE DOOR BEYOND 1 FOOT. AFTER EXERCISING THE DOOR A COUPLE OF TIMES THE CREW WAS ABLE TO GET THE DOOR TO OPEN FULLY. THE DOOR FEELS AS THOUGH CABLES HAVE BECOME LOOSE INSIDE THE DOOR. OPENED THE MAIN CABIN DOOR AND VERIFIED THAT THE POWER ASSIST CABLE HAD MOVED AWAY FROM THE PULLEY. INSPECTED THE PULLEY ASSEMBLY FOR PLAY AND THE POWER ASSIST CABLE FOR FRAYING, NO DEFECTS WERE NOTED. REATTACHED THE POWER ASSIST CABLE AND BEGAN TO PERFORM AN OPERATIONAL CHECK OF THE MAIN CABIN DOOR FROM THE OUTSIDE. THE POWER ASSIST CABLE MOVED SMOOTHLY AROUND THE PULLEY WHILE OPENING THE MAIN CABIN DOOR OPEN AND CLOSED. WE THEN PUT POWER TO THE AIRCRAFT PROCEEDED TO PERFORM OPERATIONAL CHECK OF THE DOOR FROM THE INSIDE OF THE CABIN AND VERIFIED SMOOTH OPERATION OF THE MAIN CABIN DOOR ASSEMBLY. ALL WORK WAS PERFORMED WITH REFERENCE TO CL-650 AMM 52.-. 11-19, NO FURTHER DEFECTS NOTED. AIRCRAFT OK FOR SERVICE.
DURING FLIGHT, CREW SMELLED FUMES IN THE CABIN AND COCKPIT. FUMES SMELLED LIKE OIL OR FUEL WITH THE STRONGEST SOURCE COMING FROM THE AFT PORTION OF THE AIRCRAFT. THIS OCCURRED SEVERAL MINUTES AFTER APU SHUT DOWN. FUMES BEGAN TO DISSIPATE AS THE DESCENT OCCURRED. FOUND FUEL LEAKING FROM THE APU FUEL SHUTOFF SOLENOID VALVE. FUEL FUMES WERE GETTING PICKED UP BY THE APU AND SENT INTO THE CABIN AND COCKPIT. REPLACED SOLENOID VALVE AND LEAK CHECK OK. REPLACED THE LEFT AND RIGHT CONDENSER BAGS. LEAK CHECK OK. NO FUMES IN COCKPIT OR CABIN NOTED. WORK PERFORMED IAW SMM 49-31-07 AND 21-51-13.