N705QS

ATA 5210

Part: DOOR — FAULTED (ZONE 800) · airframe 7,197 hrs · 4,124 cycles

UPON ARRIVAL TO AIRCRAFT, COULD NOT ACCESS CABIN THROUGH MAIN DOOR BECAUSE THE DOOR HANDLE WAS JAMMED BETWEEN THE CLOSED AND HALF WAY OPEN POSITION. HANDLE WOULD NOT LIFT PASSED THE HALF WAY POINT. COULD HEAR BINDING AND CLICKING WHEN TRYING TO OPEN FULLY. CORRECTIVE ACTION: MED CURTAIN CAUGHT ON HANDLE. CURTAIN REPOSITIONED. OPS CHECK GOOD. IAW AMM 52-11-00.

ATA 2910

Part: PUMP — DAMAGED (HYD SYSTEM) · airframe 3,851 hrs · 2,148 cycles

AT F410 DURING CRUISE FLIGHT, NOTICED AN ABRUPT VIBRATION ACCOMPANIED BY A LOUD RUMBLE. THE HYD SYNOPTIC PAGE SHOWED 2 PERCENT FLUID LEVEL ON LEFT SYSTEM. DIVERTED TO KIAD. WHEN WE SELECTED GEAR DOWN AN AMBER L HYD PRESS LOW CAS ILLUMINATED. FOLLOWED QRH AND LANDED. TOWED TO THE RAMP DUE TO NO NWS. NOTICED HYD FLUID DRIPPING FROM LT ENGINE ON POST FLIGHT. FOUND LT EDP TO HA VE OVERHEATED AND MELTED LTS GASKETS. REMOVED DAMAGED LT ENGINE DRIVEN HYDRAULIC PUMP AND INSTALLED REPAIRED UNIT IAW AMM 29-12-01. OPS AND LEAK CHECKED GOOD. DUE TO OVERHEAT, COMPLIED WITH LEFTHYD.RAUUC SYSTEM OVERHEAT CHECK IAW AMM 29-10-00. ORIG SUBMISSION DATE: 1/16/2023

ATA 7931

Part: PUMP — FAILED (OIL SYSTEM) · airframe 1,171 hrs · 675 cycles

DURING DESCENT AT 10000 FT RED RT ENGINE OIL PRESS LOW CAS MESSAGE DISPLAYED. WE DID THE APPROPRIATE QRH PROCEDURE AND SHUT THE ENGINE DOWN. CORRECTIVE ACTION: PERFORMED HONEYWELL SIL D204801000001 REV 1 DATED 12 JAN 2018 AND FOUND ENGINE OIL PUMP FAILED. REMOVED ENGINE OIL PUMP P/N 3038704-6 S/N 18-162407-00789. INSTALLED OVERHAULED PUMP DETAILED ABOVE. OPERATIONS CHECKS AND LEAK CHECKS GOOD AT THIS TIME INSTALLED P/N 3038704-6 S/N 14-162407-00421.

ATA 5300

Part: UNKNOWN — VIBRATION (FUSELAGE) · airframe 9,082 hrs · 5,524 cycles

AT FL210, HAD AN AIRFRAME VIBRATION NOTICED AT 300 KIAS AND INCREASED AS AIRSPEED INCREASED. INTENSITY INCREASED IN LT TURNS, CLIMBS, DESCENTS, AUTO-PILOT ON & OFF, YAW DAMPER ON & OFF, RUDDER BIAS ON & OFF. HAD NO EFFECT. THERE WAS NO ABNORMAL VIBRATION IN THE YOKE OR RUDDER PEDALS.

ATA 3400

Part: MONITOR — SHORTED (CABIN) · airframe 6,409 hrs · 3,818 cycles

WHILE ENROUTE, PAX NOTIFIED CREW THAT THERE WAS SMOKE IN THE CABIN, TURNED AROUND, THERE WAS A PLUME OF SMOKE COMING FROM THE NR 4 AIRSHOW MONITOR. SHUTDOWN CABIN ELECTRICAL POWER AND DIVERTED. CHECKED WIRING FROM MASTER CONTROLLER CONNECTOR PIN "U" TO PINS 2, 19, AND 35 ON CONNECTOR WITH NO DEFECTS NOTED. WITH POWER APPLIED, VERIFIED 25 VDC ON ABOVE PINS ON CONNECTOR CHECKED AND POWER & GROUND CHECKED IAW DWG GCB15020007 REV "C" WITH NO DEFECTS NOTED. R & R THE A/V CONTROLLER, MONITOR AND MONITOR RECEPTACLE. PERFORMED OPS CHECK WITH NO DEFECTS NOTED. WORK COMPLETED IAW DWG GCB45007REV "C".

ATA 2840

Part: WARNING LIGHT — ILLUMINATED · airframe 5,570 hrs · 3,294 cycles

TAKEOFF WAS ABORTED AT APPROX 30 KTS BOTH L/R (FQMC) LIGHTS CAME ON AND LT WING TANK SHOWED AMBER "ZERO'S". INDICATIONS WENT BANK TO NORMAL WHEN WE STOPPED ON THE TAXI WAY, TAXING BACK TO THE FBO BOTH LIGHTS CAME BACK ON AGAIN.

ATA 3417

Part: ADC — DAMAGED · airframe 5,570 hrs · 3,294 cycles

DEBRIEFED PILOT'S AND CHECKED MAINTENANCE DATA FOR ANY LRU FAULTS PRIOR TO SHUTDOWN. CHECKED LRU STATUS AND HISTORY WITH NO FQMC FAULTS FOUND. CHECKED LRU DIAGNOSTICS AND NOTED BOTH FQMCS INDICATING NORMAL CONDITION CODES. WORK DONE PER AMM 45-20-06. SUMPED ALL DRAIN POINTS ON THE ACFT WITH NO WATER FOUND. PERFORMED FQMC TEST WITH PUSHBUTTON ON MAINTENANCE PANEL BY CO-PILOT'S LEG AND NOTED ALL CORRECT INDICATIONS. PERFORMED TEST FUNCTION ON REFUELING PANEL WITH PASS RESULT. PERFORMED RING OUT OF WOW INPUTS BETWEEN FQMC AND THE LEFT HAND WOW SWITCH, ALL WIRES METERED GOOD, 0.4 OHMS ON GROUND AND OPEN IN AIR MODE. WORK PERFORMED IAW WDM 28-40-00. REMOVED SUSPECTED FAULTY FQMC P/N 4AS8840001-005, S/N 0065. OPERATIONAL CHECK GOOD. ALL WORK DONE IAW CMP 284101.

ATA 2780

Part: WARNING LIGHT — FALSE ACTIVATION (KRUEGERS) · airframe 5,342 hrs · 3,156 cycles

FOLLOWING A NORMAL TAKEOFF, SLATS WERE RETRACTED. SLATS RETRACTED NORMALLY, KRUGERS INDICATED UNBALANCED. AFTER THE FLIGHTCREW RESET THE AOC, AOA, AND PROBE LIGHTS VISUALLY INSPECTED RETRACTED SLATS AND KRUEGERS. THEN OPERATED THE SLATS AND KRUEGERS TO OBSERVE THE EICAS INDICATIONS. OPERATED NORMALLY AT THIS TIME. THEN EXTENDED KRUEGERS TO VISUALLY INSPECT NOTHING NOTED FLTD THE KRUEGERS AGAIN TO CHECK THE TIME TO RETRACT AND EXTEND. THEY FALL WITHIN LIMITS IAW MM 27-52-00 COULD NOT DUPLICATE SQUAWK AT THIS TIME.

ATA 2780

Part: SLAT SYSTEM — MALFUNCTIONED · airframe 5,342 hrs · 3,156 cycles

FOLLOWING A NORMAL TAKEOFF, SLATS WERE RETRACTED. KRUGERS INDICATED UNBALANCED, IN AMBER.

ATA 3100

Part: MONITOR — INOPERATIVE (COCKPIT) · airframe 4,027 hrs · 2,365 cycles

DURING POST FLIGHT, EVALUATING INOP VIDEO MONITOR SCREEN. SCREEN WAS MOVED TO VIP STATION TO DETERMINE IF MONITOR CONNECTOR WAS CONNECTED OR MONITOR ITSELF WAS INOPERATIVE. IMMEDIATELY AFTER MONITOR WAS PLUGGED IN AT VIP SEAT SMOKE WAS NOTED AT THE CONNECTION. COMPLIED WITH REPLACEMENT OF MONITORS AND CONNECTOR CABLES WHICH WERE ON HAND. REPLACED MISSING MONITOR IN AIRCRAFT. OPS CHECKED THE OTHER FOUR MONITORS BY PLUGGING THEM INTO A WORKING POSITION AND VERIFYING VIDEO. CONNECTORS ON THE MONITORS AND MATING CONNECTORS ALL CHECKED NORMAL.