N452QS

Part: SKIN — DENTED (ZONE 500)

BIRD STRIKE TO LEADING EDGE OF LEFT WING APPROX 3 FEET OUTWARD FROM FUSELAGE. THERE IS A NOTICEABLE DENT. INSTALLED REPAIRED LEADING EDGE IAW AMM 57-40-00. LEADING EDGE ALL OPS AND LEAK CHECKS SATISFACTORY.

Part: CONTROL UNIT — FAULTY (BRAKES) · airframe 2,640 hrs · 2,009 cycles

WORN BRAKES: ON TAXI OUT NOTICED BRAKES WERE NOT ENGAGING WELL AND HAD A STRONG VIBRATION. FELT LIKE INTERMITTENT APPLICATION AND STRUGGLING TO GRAB. CORRECTIVE ACTION: REPLACED BRAKE CONTROL UNIT IAW EMB PH300 AMM 32-41-01 OPS CHECK GOOD

Part: COMPUTER — FAULTED (ZONE 700) · airframe 2,608 hrs · 1,986 cycles

DURING TAXI BOTH L & R BRAKES CHATTERED, PULSED AND WERE VERY GRINDY. MORE PRONOUNCED WITH LIGHT APPLICATIONS OF THE BRAKES. TAXI SPEEDS WERE UP TO 25KTS AND HAPPENED AT ALL SPEEDS. ALSO A SLIGHT BURNING SMELL FROM THE BRAKES UPON RETURN TO THE FBO. CORRECTIVE ACTION: LH AND RH BRAKE LIFE SATISFACTORY. NO DAMAGE OR LEAKS NOTED. HYDRAULIC RESERVOIR IN THE GREEN. RIGHT HAND TIRE LOOKS NEW AS DOES THE BRAKE WITH NO LEAKS. CUSTOMER REQUESTED CVDR DOWNLOAD BEFORE FURTHER MAINTENANCE AYKUT TAN 05/29/2025 PERFORMED NJA BRAKE AND EMERGENCY/PARKING BRAKE SYSTEM BLEED FORM TC-E50-32-1001 REV 0, DATED 21 5EPT2022, FOUND AIR IN LH MAIN BRAKE. RH BRAKE NORMAL, CREW PERFORMED TAXI BRAKE CHECK. NO CHATTERING OR DEFECTS NOTED FROM CREW AND MAINTENANCE, BRAKE SYSTEM OPERATION NORMAL. NO FURTHER DEFECTS NOTED

Part: BATTERY PACK — DEFECTIVE (ZONE 200) · airframe 2,039 hrs · 1,561 cycles

EMERGENCY LIGHTS BATTERY: EMERGENCY LIGHTS STAY ON WITH SWITCH IN ARMED POSTION. AFTER A FEW MINUTES LIGHTS START TO BLINK. CORRECTIVE ACTION: REPLACED EMERGENCY BATTERY PACKS PN 7450LS-00 SN 005917 & SN 005920 IAW EMB-505 AMM 33-52-01-400-801-A. OPS CHECK GOOD.

Part: CONTROL UNIT — FAULTED (BRAKE SYS) · airframe 1,648 hrs · 1,264 cycles

DURING TAXI OUT RIGHT BRAKE WAS BINDING. RETURNED TO FBO AND RECEIVED A BRK FAIL CAS MESSAGE UPON SETTING THE PARKING BRAKE. REMOVED FAULTY BRAKE CONTROL UNIT P/N OAP00100-11, SN 352960458 AND REPLACED IT WITH MODIFY BCU, AND PERFORMED SATISFACTORY OPERATIONAL CHECKS. ALL MAINTENANCE PERFORMED IAW AMM 32-41-01-400-801-A. NO FURTHER DEFECTS NOTED AT THIS TIME.

Part: SEAL — DAMAGED (ZONE 500) · airframe 938 hrs · 729 cycles

AIRFRAME VIBRATION: DURING FLIGHT ABOVE 250 KNOTS AT ALL ALTITUDES THE AIRCRAFT VIBRATED AND CREATED A LOUD VIBRATION NOISE THROUGHOUT THE CABIN. THE INTENSITY OF THE VIBRATIONS AND NOISE INCREASED DURING DECENT AND INCREASE OF SPEED. THE CABIN WALL ALONG THE LEFT WING SEEMED TO VIBRATE MORE INTENSELY. PLEASE EVALUATED FOR STRUCTURAL VIBRATIONS. //SIGNOFF// PERFORMED THE AIRCRAFT NOISE AND VIBRATION INSPECTION, REFERENCE EMBRAER PHENOM 300 AMM 05-50-27 TABLE 601, I ELIMINATED THE PROBABLE CAUSES OF THIS DISCREPANCY. ACCORDING TO THE DISCREPANCY THIS VIBRATION HAPPENED IN ALL PHASES OF FLIGHT, GEARS WERE RETRACTED, FLAPS WERE UP, CREW DIDN'T MENTION ANYTHING ABOUT THE VCS, AND NO VIBRATION IN FLIGHT CONTROLS. THIS ONLY LEAVES THE ENGINES AND ALL THE SEALS ON THE AIRCRAFT INCLUDING THE MAIN ENTRY DOOR/EMERGENCY DOOR, CHECKED BOTH ENGINE FAN AND BLADES FOR DEFECTS. NONE FOUND. PERFORMED INSPECTION OF THE STARTER/GENERATOR ON THE LH ENGINE DUE TO THE FACT THAT THE VIBRATION WAS MORE PRONOUNCED ON THE LEFT SIDE. NO DEFECTS NOTED. PERFORMED HIGH POWER ENGINE RUNS WITH NO VIBRATION DETECTED. CHECKED ALL SEALS ON THE AIRCRAFT AND LOWERED FLAPS. FOUND THE LH INBOARD FLAP SEAL BETWEEN THE FLAP AND THE FUSELAGE RIPPED. REPLACED SEAL AND PERFORMED OPERATIONAL CHECK OF THE FLAPS. NO DEFECTS NOTED. EVEN THOUGH THE GEARS WERE RETRACTED, PERFORMED GEAR SWINGS TO ELIMINATE THE GEARS BEING THE CAUSE. NO DEFECTS NOTED. COMPLETED THE INSPECTION. ORIG SUB DATE: 8/11/2023

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 745 hrs · 574 cycles

EMERG EXIT DOOR: THE EMERGENCY EXIT DOOR IS NOT SEATED PROPERLY. FROM THE INSIDE OF THE CABIN THE TOP RIGHT CORNER IS PUSHED IN ABOUT 1/2 INCH AT THE WIDEST POINT. YOU CAN SEE SUNLIGHT SHINNING BETWEEN THE DOOR AND SIDE WALL PANEL ON THE LEFT INSIDE OF THE DOOR//CORRECTIVE ACTION//VERIFIED EMERGENCY DOOR NOT SEATED PROPERLY. UPON INTIAL INSPECTION FOUND TOP AND AFT PORTION OF INTERIOR PANEL OF EMERGENCY DOOR WEDGED BETWEEN CABIN PANEL CAUSING DIFFICULTY OPENING EMERGENCY DOOR. RE-SEATED DOOR PROPERLY AS REQUIRED. EMERGENCY DOOR NOW FITS AS SHOULD. NO DEFECTS NOTED. WORK DONE IN REF WITH PHENOM 300 AMM 52-20-00.

Part: DOOR — LACK OF LUBE · airframe 321 hrs · 241 cycles

MAIN DOOR: MAIN CABIN DOOR VERY DIFFICULT TO OPEN FROM INSIDE AND OUTSIDE OF AIRPLANE. " CORRECTIVE ACTION" OPENED THE MAIN ENTRY DOOR AND VERIFIED THAT THE DOOR WAS DIFFICULT TO OPEN. WITH THE DOOR OPEN EXTENDED AND RETRACTED THE MED DOOR PINS WITH DOOR HANDLE. FOUND THE HANDLE TO BE STIFF DUE TO HOW NEW THE AIRCRAFT IS. LUBRICATED THE MED DOOR PINS AND CYCLED THE DOOR HANDLE AGAIN. THE DOOR HANDLE CYCLED EASIER THIS TIME. LUBRICATED DOOR PINS AND CYCLED MULTIPLE TIMES. PERFORMED OPENING AND CLOSING PROCEDURE FOR THE MED. THE DOOR NOW OPENS AND CLOSES EASILY. CONTACTED MCC. MCC ELECTS TO SIGN OFF DUE TO OPS CHECKS GOOD. WORK DONE IAW EMB-505 AMM 52-00-00

Part: WINGLET — CORRODED (ZONE 600) · airframe 11,386 hrs · 5,603 cycles

RIGHT WINGLET CORRODED IN ATTACH BORE, REF W/O 2142.23.3-23.6 FOR REPAIR.

Part: ENGINE — VIBRATION (NR 1) · airframe 10,952 hrs · 5,396 cycles

NR 1 ENGINE DISPLAYED HIGH VIBRATION, IE LP 2.25, IN FLIGHT. PRECAUTIONARY SHUTDOWN AND LANDING WITHOUT FURTHER INCIDENT. INSPECTED AIRCRAFT, NO DEFECTS NOTED.

Part: RESERVOIR — LEAKING (HYD SYSTEM) · airframe 10,763 hrs · 5,312 cycles

AMBER "COMBINED HYD QUANTITY" CAS MESSAGE AT FL410. THE COMBINED HYD SYS QTY INDICATION (EICAS) READS ZERO. THE FUSELAGE COMBINED SYS GAUGE ALSO READS ZERO. NO HYD FLUID FOUND IN EQUIPMENT BAY OR OUTSIDE FUSELAGE. R & R THE COMBINED HYD RESEVOIR & FOUND SATISFACTORY.

Part: ACTUATOR — LACK OF LUBE (TE FLAPS) · airframe 10,629 hrs · 5,245 cycles

FLAPS FAILED TO FULLY RETRACT AFTER TAKEOFF, FLAPS STUCK AT 10. OPERATED FLAPS NUMEROUS TIMES, NO DEFECTS NOTED. OBSERVED FLAP ACTUATOR SCREWS WERE DRY WITH NO LUBE. LUBRICATED ALL FOUR FLAP ACTUATORS AND TRAVEL NUTS. COMPLIED WITH FLAP RIGGING CHECKS, NO DEFECTS NOTED. WORK PERFORMED IAW MM 27-20-00 AND 27-06-00.

Part: BOLT — CORRODED (WING) · airframe 9,899 hrs · 4,881 cycles

MOST CADMIUM PLATED HARDWARE INSTALLED IN WING INTERGRAL FUEL TANKS HAVE DEVELOPED CORRSION. HARDWARE REQUIRES REPLACEMENT MULTIPLE PNS AFFECTED.

Part: TORQUE TUBE — CORRODED (RUDDER) · airframe 7,422 hrs · 3,692 cycles

CORROSION WAS FOUND ON RUDDER TORQUE TUBE, UNIT REPLACED.