N514QS
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
RIGHT HORIZONTAL STAB TIP HAS PAINT EROSION.
LEFT MLG WHEEL WELL AFT LOWER SPAR CAP HAS CORROSION.
EMERGENCY EYE LIGHT OVER SEAT 7 AS WELL AS THE RIGHT OVER WING EXIT LIGHTS ARE NOT ILLUMINATING WHEN BOTH BATT SWITCHES ARE OFF. INSPECTED BATTERY PACK #3 (UF903) AND FOUND EXCESSIVE HEAT EMANATING FROM CASE AN HOUR AFTER FLIGHT LANDED. REMOVED AND REPLACED BATTERY PACK NR 3 IAW AMM 33-50-06 OPS CHECK GOOD NO OTHER DEFECTS NOTED.
WITH THE EMER LIGHT SWITCH IN THE ON OR ARM POSITION AND THE BATTERIES OFF, NONE OF THE EMER LIGHTS WILL ILLUMINATE. REMOVED AND REPLACED NO.4 EMERGENCY BATTERY PACK IAW MM 33-50-06. REMOVED AND REPLACED NO.1 EMERGENCY BATTERY PACK IAW MM 33-50-06. ACCOMPLISHED EMERGENCY LIGHTING OPERATIONAL CHECK IAW MM 33-50-00. OPS CHECK GOOD.
DURING CRUISE AT FL430 WITH RAT OF -39 RECEIVED AN AMBER ENG CNTRL FAULT L CAS MESSAGE. ALONG WITH THIS CAS MESSAGE WE RECEIVED THE R ENG. THE ENG CNTRL FAULT QRH PROCEDURE (U1) COMPLETED. PROCEDURE INDICATED TO LAND AND CONTINUED TO DESTINATION. DURING DESCENT, EXPERIENCED AN ENG SURGE & VIBRATION. SHUTDOWN RT ENG USING THE INFLIGHT ENGINE SHUTDOWN QRC. CONFIRMED RT ENG SURGING. AFTER RT ENG SHUT DOWN, EXPERIENCED SAME SURGE & VIBRATION COMING FROM LT ENGINE & DID AN EMERGENCY LANDING. REMOVED LT ENG. COMPLETED MX STAND BUILD UP OF REPLACEMENT ENG & INSTALLED THE REPLACEMENT ENG IAW AMM 71-00-05 AND EMM 71-00-00. REMOVED RT ENG. ACCOMPLISHED INSTALLATION OF NEW ENG IAW AMM 71-00-05 & EMM 71-00-00.
EMER LIGHTS FAIL DURING CHECK AS WELL AS WITH MAIN DC POWER APPLIED AND EMER LIGHT SWITCH TO "ON" POSITION. FAILED LIGHTS ARE AS FOLLOWS: PATH LIGHTS 5&8, ALSO #7 OVER SEAT LIGHT AND OVER WING EVACUATION LIGHT. FOUND FUSE OF EMERGENCY LIGHT BATTERY PACK #3 BLOWN DUE TO PATHWAY LIGHT AT SEAT #8 WIRES WERE CHAFFED. LIGHT ASSEMBLY AND WIRING WAS REPLACED UNDER SQUAWK #13 OF THIS WORK ORDER. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY PACK #3 FUSE PER RADIANT POWER CORP CBS28-1 CMM 24-31-05. ALL EMERGENCY LIGHTS OPS CHECKS GOOD PER MM 33-50-00.
AMBER DOOR OPEN LIGHT ON DOOR NOT WORKING. R & R MAIN CABIN DISC HARNESS IAW WM 52-70-10 OPS CHECK GOOD.
SB680A-25-15 (REPLACEMENT OF THE SMOKING/FASTEN SEAT BELT SIGN IN THE AFT LAVATORY). STEP 4.D CONTAINS AN ERROR. THE SB STATES TO INSTALL A WIRE AND PIN INTO ALL THREE CONNECTOR SOCKETS. THE NEW LIGHT ONLY HAS 2 WIRES, SO ONE CONNECTOR SLOT IS LEFT EMPTY. ACCOMPLISHED TEXTRON AVIATION MEMO FP220406 DATED APRIL 6, 2022; ACCOMPLISH SB680A-25-15 REV. 1 WITH A CHANGE TO STEP 4.D.
BLEED AIR: ON THE GOUND PHX MAIN DOOR OPEN APU ON BLEED AIR ON CABIN FILLED UP WITH SMOKE NO CAS MESSAGES. PLS SEE VIDEO. REMOVED FAILED APU AND INSTALLED CUSTOMER SUPPLIED REPAIRED APU SERVICED OIL AS REQUIRED, UPDATED AIRCRAFT TIMES TO REFLECT THE NEW APU HOURS AND CYCLES AND PERFORMED LEAK/ OPS CHECKS, OPS CHECKS PASSED NO SMOKE IN THE CABIN, NO LEAKS FOUND RESECURED ALL ACCESS GAINED IAW CE- 680A AMM 49-10-00.
LEFT WING INBOARD FLAP DAMAGE (GOUGE). ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DQ27564M1 DATED NOVEMBER 4, 2020; 680A-0052 (N514QS) LEFT WING INBOARD FLAP DAMAGE (GOUGE).
CRACK DAMAGE, NOSE LANDING GEAR WHEEL WELL (NWW), FRAME, WEB, AND DOUBLERS, FS 75. ACCOMPLISHED TEXTRON AVIATION STANDARD REPAIR SR-680A-ATA53-25890 REV- DATED JUNE 01, 2020 AND FAA FORM 8100-9 DATED 6/1/2020. STANDARD REPAIR - CRACK DAMAGE, NOSE LANDING GEAR WHEEL WELL (NWW), FRAME, WEB, AND DOUBLERS, FS 75.
APU STINGER SKIN DAMAGE (CORROSION), REF ENGINEERING MEMO DQ26585M1 DATED AUGUST 13, 2020.
RIGHT ENGINE UPPER COWL HEAT DAMAGE, REF ENGINEERING MEMO DQ26626 DATED AUGUST 16, 2020.
NOSE LANDING GEAR INNER BORE DAMAGE (SCRATCHES), REF ENGINEERING MEMO DQ26613M1 DATED AUGUST 14, 2020.
LT LOWER & RT UPPER HORIZONTAL STABILIZER SPLICE STRIPS CORRODED.
LT & RT HORIZONTAL UPPER AND LOWER SKIN FWD OF WEDGE PANEL HAS SURFACE CORROSION.
REPAIR OF LEFT-HAND HORIZONTAL TIP CAP DAMAGE. ENGINEERING MEMO DQ24376M1 DATED 1/14/2020.
APU SMOKE - AFTER STARTING UP THE APU DURING PREFLIGHT GOT SMOKE THROUGHOUT THE AIRCRAFT. ODOR WAS LIKE AN OIL SMELL. REMOVED & REPLACED APU ASSEMBLY IAW MM 49-10-00.
NOSE GEAR GREEN LIGHT WILL NOT ILLUMINATE WITH GEAR DOWN. REPLACED NOSE LANDING GEAR CHANGE OVER SWITCH. OPS CHECK GOOD IAW THE HAWKER 1000 MM 32-60-05. REPLACED NOSE LANDING GEAR CHANGE OVER MICRO SWITCH P/N WITH NEW P/N 1EN1-14N119. PERFORMED SATISFACTORY, OPS CHECKS IAW THE HAWKER 1000 MM 32-60-05.
NOTICED FUMES AND SLIGHT SMOKE COMING FROM THE CO-PILOTS AIR CONDITIONING VENT DURING DEPARTURE, ODOR WAS STRONGEST WHEN MAIN AIR VALVES WERE FIRST OPENED AND WENT AWAY AFTER THE VALVES WERE PLACED TO LOW PRESSURE. RAN BOTH ENGINES AND APU WITH BLEED AIR ON FOR 45 MINUTES, NOTICED SLIGHT SMELL FOR FEW SECONDS. WENT FULL HOT ON CABIN HEAT ODOR DID NOT RETURN, SYSTEM OPS CHECKED GOOD IAW HAWKER 1000 MM CHAPTER 21-30-00.
AFTER TAKE-OFF COULD NOT RETRACT LANDING GEAR, ACCOMPLISHED AIR TURN BACK TO TPA AND LANDED OVERWEIGHT. - REPAIRED BROKEN WIRE AT KAPIS BY INSTALLING SPLICE P/N D436-36, OPS CHECKED GOOD I/A/W HAWKER 1000 MM CHAPTER 32-30-00. C/W PRESSURIZE CHECK ON GROUND OPS CHECKED, LEAK CHECKED GOOD IAW HAWKER 1000 MM CHAPTER 21-30-00.
DURING TAKEOFF ROLL AT APPROX 100KTS A/C STARTED YAWING TO THE RIGHT ENGINE GUAGES REVEALED LEFT N1 98.4 PERCENT RIGHT N1 94 PERCENT LEFT ENGINE FUEL FLEW 2300 LBS/HR AND RIGHT 1900 LB/HR APR ARMED.
FOUND LEFT PITOT HEAD (P1) LINE 'SAWED THROUGH' BY LEFT ELEVATOR CONTROL CABLE DURING INVESTIGATION OF AN AIRSPEED DISCREPANCY. REMOVED AND REPLACED LINE. LINE IS PART OF A 4-GANG CLUSTER RUNNING UNDER THE CENTER COCKPIT FLOOR. SUBMITTER STATED THE LINES ARE GETTING STEPPED ON WHEN THE FLOOR PANELS ARE REMOVED AND THE AREA IS EXPOSED. SUGGEST BETTER SUPPORT OF LINES.
DURING A ROUTINE INSPECTION, FOUND ELEVATOR LEVER ARM (IPC 55-20-05-01, ITEM 370) GOUGED ON THE OUTBOARD SIDE APPROXIMATELY .5 INCH ABOVE ELEVATOR ROD ATTACHEMENT BOLT. DURING REMOVAL AND INSTALLATION OF THE TAIL ASSEMBLY BULLET FAIRING, (IPC 55-30-10-01, PAGE 0) SCREWS (ITEM 10) FOR THE LEFT AND RIGHT INSPECTION PANELS (ITEMS 25 AND 30) CAN CONTACT THE ELEVATOR ACTUATING LEVER ESPECIALLY IF LONGER SCREWS ARE INSTALLED. FOUND LONGER SCREWS HAD BEEN INSTALLED IN SEVERAL LOCATIONS ON THIS PANEL.
FOUND CRACK ON LEFT ENGINE THRUST REVERSER UPPER DOOR INBOARD LONGERON ASSEMBLY ABOUT TWO INCHES FROM BUMPER. LONGERON ASSY IS WEAK IN MACHINED AREA WHICH IS WHERE THE CRACK IS LOCATED. SUBMITTER STATED IF THE BUMPER IS MODIFIED TO EXTEND PAST THE WEAK AREA, THE PROBLEM WILL PROBABLY GO AWAY.