N523QS

Part: SEAL — UNKNOWN (PAX DOOR) · airframe 7,315 hrs · 4,853 cycles

LOUD SQUEAL HEARD DURING DECENT FROM 7500 FT ALL THE WAY DOWN TO 5000 FT. 2.7 PRESSURE DIFFERENCE WHEN SQUEALING STOPPED. NO SQUEAL DURING CLIMB OR CRUISE. CABIN DOOR SEAL DETAILED INSPECTION CARRIED OUT WITHOUT FINDINGS IAW MM 52-10-00-222 REV.20. APU PRESSURIASTION RUN CARRIED OUT AS PER TEXTRON`S EMAIL. NO FAULTS FOUND. CREW TO REPORT FURTHER.

Part: NONE — NONE · airframe 5,399 hrs · 3,589 cycles

MAIN EXIT SIGN/LIGHT: MAIN DOOR EXIT SIGN LIGHTS REMAIN ON REGARDLESS OF SWITCH POSITION. // SIGNOFF// FOUND #1 EMERGENCY LIGHTING INERTIA SWITCH TO BE TRIPPED. RESET #1 EMERGENCY LIGHTING INERTIA SWITCH. PERFORMED EMERGENCY LIGHTING INERTIA SWITCH OPS CHECK IAW CE-680A MM 33-50-00. OPS CHECK GOOD.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 4,308 hrs · 2,877 cycles

CABIN EMERG LIGHT: WHEN PLANE POWERED UP WITHIN 20 MINS OF SHUTDOWN, THE FOLLOWING EMERGENCY LIGHTS FAILED TO ILLUMINATE: FLOOR SEAT 5 & 8, OVER WIND RIGHT SIDE, AND OVERHEAD SEAT 7 (VERY DIM) WHEN APU STARTED , ALL LIGHTS ILLUMINATED BUT EXTINGUISHED SHORTLY AFTER SHUTDOWN.

Part: BATTERY — FAULTY (EMERGENCY LIGHTS) · airframe 4,308 hrs · 2,877 cycles

CABIN EMERG LIGHT: WHEN PLANE POWERED UP WITHIN 20 MINS OF SHUTDOWN, THE FOLLOWING EMERGENCY LIGHTS FAILED TO ILLUMINATE: FLOOR SEAT 5 & 8, OVER WIND RIGHT SIDE, AND OVERHEAD SEAT 7 (VERY DIM) WHEN APU STARTED , ALL LIGHTS ILLUMINATED BUT EXTINGUISHED SHORTLY AFTER SHUTDOWN. ***CORRECTIVE ACTION*** GAINED ACCESS TO AND REMOVED INOP #3 EMERGENCY BATTERY AND INSTALLED REPAIRED CONDITION #3 EMERGENCY BATTERY IAW CE680A AMM 33-50-06. PERFORMED 2HR BATTERY CHARGING PROCEDURE IAW CE680A AMM 33-50-00 SECTION C. TECHS ALLOWED EMERGENCY BATTERIES TO STABILIZE FOR L0MIS AFTER THE 2HR CHARGE. TECHS PERFORMED EMERGENCY LIGHTS OPS AND FUNCTIONAL CHECKS IAW CE680A AMM 33-50-00. OPS AND FUNCTIONAL CHECKS GOOD WITH NO DEFECTS NOTED.

Part: COVER — CORRODED (NR 2 ACCESSY G/B)

#2 ENGINE ACCESSORY GEAR BOX REAR COVER HAS MULTIPLE AREAS OF CORROSION. TEMPORARY REPAIR AND PROTECTION OF THE AGB COVER FLANGES FROM MINOR CORROSION IAW P&WC 306D1 MM 72-60-01 REV. 17.

Part: GEARBOX — CORRODED (NR 1 ACCESSORY)

#1 ENGINE ACCESSORY GEARBOX REAR COVER HAS CORROSION IN MULTIPLE AREAS. TEMPORARY REPAIR AND PROTECTION OF THE AGB COVER FLANGES FROM MINOR CORROSION IAW P&WC 306D1 MM 72-60-01 REV. 17.

Part: DOOR — OUT OF ALIGNMENT · airframe 3,744 hrs · 2,486 cycles

MAIN DOOR: CABIN DOOR WILL NOT CLOSE UNTIL AFTER THE CANCEL BUTTON IS PRESSED. THEN DOOR OCCASIONALLY STOPS HALF WAY UP, THEN CONTINUES. // SIGN OFF // INSPECTED FOUND UPPER PART OF SEAL (AIRFRAME SIDE) WAS OUT OF TRACK, RESECURED THE SEAL, COMPLIED WITH OPS CHECK SEVERAL TIMES, OPS CHECK GOOD WITHOUT ANY DEFECT .ALL WORK ACCOMPLISHED PER CE-680A AMM 52-10-00.

Part: DOOR — MALFUNCTIONED (MAIN PAX) · airframe 3,744 hrs · 2,486 cycles

MAIN DOOR: CABIN DOOR WILL NOT CLOSE UNTIL AFTER THE CANCEL BUTTON IS PRESSED. THEN DOOR OCCASIONALLY STOPS HALF WAY UP, THEN CONTINUES.

Part: ACTUATOR — FAILED (PRECOOLER) · airframe 3,370 hrs · 2,257 cycles

ON DESCENT, STARTED TO SMELL A LIGHT BURNING SMELL IT WAS FOLLOWED BY AN AMBER BLD AIR O TEMP R CAS MESAGE. WE RAN THE CHECKLIST AND THE CAS MESSAGE WENT OUT. THE SMELL WENT AWAY. AFTER A FEW MINUTES THE BURNING SMELL RETURNED, SO WE JUST TURNED THE RIGHT BLEED VALVE OFF FOR THE REMAINDER OF THE FLIGHT AND THE SMELL WENT AWAY. SIGN OFF. REMOVED PRECOOLER PANEL TO THE PRECOOLER VALVE, INSPECTED VALVE AND ACTUATOR NO DEFECTS NOTED, ARIES DOWNLOAD SHOWED THE FAULT BUT CAN NOT TELL IF IT WAS THE VALVE OR TEMP SENSOR, CONTACTED AMCC AND THEY WOULD LIKE BOTH THE VALVE AND TEMP SENOR CHANGED 9-00 VALVE 1 TEMP SENSOR, AND SCREWS TEMP INSTALLED PRECOOLER VALVE PANEL AND CLOSED UP ACFT. PERFORMED OPS CHECK OF RT BLEED AIR SYSTEM & VERIFIED PRECOOLER ACTUATOR MOVES. REMOVED & REPLACED RT BLEED AIR TEMP SENSOR (TT004), IAW CE-680A MM 36-10-45. OPS CHECKS GOOD. REMOVED & REPLACED RT PRECOOLER TEMP CONTROL ACTUATOR, IAW CE-680A MM 36-10-35. PERFORMED OPS CHECK, OPS CHECKS GOOD. PERFORMED HIGH POWER ENGINE RUN WHILE MONITORING PRECOOLER TEMP IN THE CDMS & VERIFIED THAT THE PRECOOLER TEMP BEGAN TO DROP ONCE 250*C WAS REACHED. NO BURNING SMELL WAS NOTED DURING ENGINE RUN.

Part: DOUBLER — CRACKED (NLG WW) · airframe 3,176 hrs · 2,113 cycles

CRACK DAMAGE, NOSE LANDING GEAR WHEEL WELL (NWW), FRAME, WEB, AND DOUBLERS, FS 75. ACCOMPLISHED FIELD REPAIR SR-680A-ATA53-25890 REV- DATED JUNE 1, 2020 AND 8100-9 DATED 6/1/2020; STANDARD REPAIR - CRACK DAMAGE, NOSE LANDING GEAR WHEEL WELL (NWW), FRAME, WEB, AND DOUBLERS, FS 75.

Part: FAIRING — DELAMINATED (RIGHT) · airframe 2,964 hrs · 1,981 cycles

LOWER FAIRING (RIGHT SIDE) DAMAGE, ENGINEERING MEMO DQ2744M1 DATED FEBRUARY 13,2020,

Part: CDU — FAULTY (COCKPIT) · airframe 10,525 hrs · 6,880 cycles

BURING ELECTRICAL SMELL IN COCKPIT, NO OTHER INDICATIONS. GEN 1 AMPS 80/ GEN 2 AMPS 120. REMOVED NR 1 FMS CDU DUE TO NO DISPLAY AND FAINT BURNING ELECTRICAL SMELL. REPLACED WITH SERVICEABLE FMS CDU OPS CHECK GOOD IAW HAWKER 1000 MM CH 34-61-00 REV 27 10/04. OPS CHECKED NR 1 AND NR 2 GENERATORS AMP SPLIT WITHIN LIMITS PER HAWKER 1000 MM CH 24-30-07.

Part: MASTER CYLINDER — OVERSERVICED (BRAKE ASSY) · airframe 9,026 hrs · 5,937 cycles

NO BRAKING ACTION FROM CO-PILOT'S RIGHT BRAKE PEDAL (ONLY 300-400 PSI REGISTERED ON BRAKE PRESS. GAUGE). - BLED HYDRAULIC SYSTEM AND SERVICED MASTER CYLINDER TO PROPER FLUID LEVEL.