N304QS

Part: STRUT — ABNORMAL (ZONE 800) · airframe 9,149 hrs · 7,143 cycles

MAIN DOOR: THE MAIN CABIN DOOR GAS STRUTS DO NOT APPPEAR TO BE OPERATIONAL. THE DOOR OPENS ABRUPTLY AND THE WIEGHT OF THE DOOR CAUSES IT TO SLAM OPEN. CORRECTIVE ACTION; ADJUSTED MED BALANCNG MECHANISM. COMPLIED WITH MULTIPLE OPS CHECK OF THE DOOR AND DOOR IS NOW OPS CHECKING GOOD. WORK PERFORMED PER EMB PHENOM 300 AMM 52-10-00

Part: BATTERY — INOPERATIVE (ZONE 200) · airframe 8,958 hrs · 7,007 cycles

CABIN EMERG LIGHT: DURING CRUISE FLIGHT AROUND 14,000' WE NOTICED THE CABIN EMERGENCY LIGHTS FLICKERING ON AND OFF RAPIDLY. WE ATTEMPTED TO CHECK THE PLACEMENT OF THE SWITCH TO ENSURE IT WAS SECURELY IN THE AUTO POSITION. THE LIGHTS CONTINUED OFF AND ON UNTIL AIRCRAFT SHUTDOWN ON THE RAMP. REMOVED AND REPLACED FWD EMERGENCY LIGHT BATTERY REF EMB AMM 33-52-01; OPS CHECKED GOOD

Part: HANDLE — BROKEN (MAIN DOOR)

WHILE OPENING THE MAIN CABIN DOOR, THE DOORHANDLE BROKE OFF. THE DOORHANDLE IS ON THE COUNTER DIRECTLY IN FRONT OF THE DOOR. CORRECTIVE ACTION: REMOVE AND REPLACED MED DOOR HANDLE IAW AMM 52-11-24. OPS AND LEAK CHECK GOOD AT THIS TIME. REPLACED MCD MICROSWITCH LEVER PER PHENOM 300 AMM 52-71-20. HANDLE PN OFF 505-09870-403 S/N UNK, SWITCH PN OFF JE-17 S/N NSN

Part: BATTERY — FAULTED (UNKNOWN) · airframe 8,181 hrs · 6,396 cycles

CABIN EMERGENCY LIGHTS FLICKERING IN FLIGHT. REMOVED AND REPLACED BOTH EMERGENCY LIGHTING BATTERY PACKS DUE TO FLICKERING IN FLIGHT, OPS CHECKS GOOD, CHARGED BATTERY PACKS, ALL WORK DONE IAW AMM 33-52-01.

Part: SHIMMY DAMPENER — DEFECTIVE · airframe 7,492 hrs · 5,869 cycles

ON LANDING AS BRAKES WERE APPLIED EXPERIENCED AN EXTREMELY VIOLENT VIBRATION COMING FROM THE NOSE LANDING GEAR ACCOMPANIED WITH EMERGENCY, BRAKE PRESSURE, LOW CAS MESSAGE. VIBRATION STOPPED AT NORMAL. TAXI SPEED WAS ABLE TO TURN OFF RUNWAY ONTO TAXIWAY WHERE HYDRAULIC LOW PRESSURE CAS BREAK FAIL CAS WITH A COMPLETE LOSS OF NORMAL AND EMERGENCY BRAKES. REMOVED AND REPLACED SHIMMY DAMPENER. PN 2117-4000-403, SN 00157. IAW PHENOM 300 AMM 32-21-06. LEAK CHECK GOOD.

Part: BATTERY — DEFECTIVE · airframe 7,021 hrs · 5,516 cycles

EMERG LIGHT SWITCH: UPON STARTUP EMERG LTSWITCH WAS PLACED TO ARM. EMERG LT NOT ARMED CAS MESSAGE EXTINGUISHED. AFTER STARTUP THE EMERG LT NOT ARMED CAS ILLUMINATED AGAIN. CREW RECYCLED SWITCH AND CAS MESSAGE EXTINGUISHED. DURING FLIGHT CREW NOTICED THAT ALL EMERG LIGHTS IN CABIN WERE ILLUMINATED AND FLICKERING. AFTER SHUTDOWN WE DETERMINED THAT THE EMERG EXIT LIGHTS TURN ON WHEN THE SWITCH IS PLACED TO ARM. AFTER A FEW MINUTES THEY START FLICKERING // SIGNOFF// REMOVED #2 EMERGENCY LIGHTING BATTERY DUE TO FAILURE. INSTALLED NEW BATTERY IN THE #2 POSITION. PERFORMED CHARGING PROCEDURE AND COMPLETED OPS CHECKS IN REF WITH EMBRAER PHENOM 300 MAINTENANCE MANUAL CHAPT 33-52-01.

Part: OUTFLOW VALVE — DEFECTIVE (CABIN PRESSURE) · airframe 6,117 hrs · 4,780 cycles

ON DEPARTURE WE EXPEREIENCED A RED CABIN RATE OF OF CLIMB OF 1000 FPM ON THE CAS. AT 13000 MSL, CABIN CONTINUED TO CLIMB TO 5600 BEFORE WE DECLARED EMERGENCY AND DIVERTED TO TJSJ. WE WENT TO MANUAL MODE PER THE QRH AND IT DID NOT WORK. THE CABIN CONTIUED TO CLIMB IN MAN MODE. AT 3000 MSL THE CABIN BEGAN TO OVERPRESSURIZE TO -500 CABIN ALT WHICH LED TO US DUMPING THE CABIN, PER THE QRH BEFORE IT GOT WORSE. WE ALSO HEARD A VIBRATING NOISE AT THE CABIN DOOR. NO EICAS INDICATIONS SHOWING DOOR WAS UNSECURE. REMOVED OUTFLOW VALVE P/N 103922-1; S/N 103922-00225. REPLACED IT WITH A "REPAIRED" OUTFLOW VALVE P/N 103922-1; S/N 103922-00596, IAW PHENOM 300 AMM 21-31-02-000-801-A/400-801-A14. COMPLETED PRESSURIZATION CHECKS, IAW PHENOM 300 AMM 21-31-00. ALL OPERATIONAL WERE GOOD NO DEFECTS NOTED.

Part: BALANCE WEIGHT — CORRODED (LT ELEVATOR) · airframe 5,870 hrs · 4,584 cycles

DURING ACCOMPLISHMENT OF EMB SB 505-55-0004 REV 01 (DATED 06/24/2020), WE NOTED THE FOLLOWING LEFT ELEVATOR MASS BALANCE WEIGHTS BELOW TOLERANCE: P/N PE915109-L42 WAS UNDER THE WEIGHT LIMITS (1027 GRAMS), AS PRESCRIBED BY THE SB (MINIMUM 1095 GRAMS) AND P/N PE915109-L33 (5 EACH) UNDER THE WEIGHT LIMITS AS FOLLOWS (3=81,1=82,1=83 GRAMS), AS PRESCRIBED BY THE SB (MINIMUM 84 GRAMS). ALL THE WEIGHTS HAVE BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED. THE ELEVATOR WAS RE-IDENTIFIED TO P/N 505-11094-615, AS PER SB INSTRUCTIONS. WE ALSO NOTED THE RT ELEVATOR MASS BALANCE WEIGHT P/N PE915109-L42 WAS UNDER THE WEIGHT LIMITS (1017 GRAMS), AS PRESCRIBED BY THE SB (MINIMUM 1095 GRAMS). P/N PE915109-L41 WAS UNDER THE WEIGHT LIMITS (2039 GRAMS), AS PRESCRIBED BY THE SB (MINIMUM 2049 GRAMS), AND P/N PE915109-L33 (2 EACH) UNDER THE WEIGHT LIMITS AS FOLLOWS (1=80,1=81 GRAMS), AS PRESCRIBED BY THE SB (MINIMUM 84 GRAMS). ALL THE WEIGHTS HAVE BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED. THE ELEVATOR WAS RE-IDENTIFIED TO P/N 505-11094-616, AS PER SB INSTRUCTIONS. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATOR’S GMM REQ.

Part: BALANCE WEIGHT — CORRODED (RT ELEVATOR) · airframe 5,524 hrs · 4,322 cycles

CORROSION ON RH ELEVATOR ADJUSTABLE MASS BALANCE WEIGHTS. REPLACED 2 EA RH ELEVATOR ADJUSTABLE MASS BALANCE WEIGHTS WITH NEW P/N PE915109-L33 IN SAME LOCATION. CORROSION ON LH ELEVATOR ADJUSTABLE MASS BALANCE WEIGHTS. REPLACED 2 EA LH ELEVATOR ADJUSTABLE MASS BALANCE WEIGHTS WITH NEW P/N PE915109-L33 IN SAME LOCATION. WORK PERFORMED PER SB505-55-A004 REV 4 DATED: NOV 21, 2019.

Part: VALVE — FAILED (COCKPIT TEMP) · airframe 5,365 hrs · 4,188 cycles

AIR DUCT - DUCT 1 OVERTEMP CAME ON IN DESCENT TO KABE WITH ALL ENGINE AND WING ANTI ICE ON. COMPLIED WITH QRH CHECKLIST. OVERTEMP DID NOT GO OUT WITH IN THE TIME LIMITS OF THE CHECK LIST. PULLED NO 1 ENGINE TO IDLE AND LANDED WITH IT AT IDLE. OVERTEMP WENT OUT BEFORE WE LANDED. FIRE DEPARTMENT INSPECTED AIRPLANE AND FOUND NO HOT SPOTS. GAINED ACCESS TO TMV IN AFT BAGGAGE AREA AND GAINED ACCESS TO COCKPIT DUCT TEMP SENSOR (DTS) IN AFT LAV AREA. PERFORMED VISUAL INSPECTION OF TMV AND DTS, NO VISUAL DEFECTS NOTED. COMPLIED WITH FIM TASK ELECTRICAL CHECKS IAW BLOCKS 2 & 3, (TABLES 201-203). ELECTRICAL CHECKS WERE GOOD. COMPLIED WITH MANUAL TEMP CONTROL MODE OPERATIONAL CHECK IAW AMM TASK 21-61-00-710-801-A. DURING CHECK IT WAS NOTED THAT THE LEFT SIDE DUCT TEMP WOULD NOT DECREASE AS RAPIDLY AS THE RIGHT SIDE AFTER TEMPERATURE WAS BROUGHT TO THE DUCT OVERHEAT WARNING THRESHOLD (APPX 115 DEGREES C). PERFORMED TEST TWICE WITH SIMILAR RESULTS. CONTACTED MANUFACTURER SUPPORT WITH FINDINGS. TECH SUPPORT RECOMMENDED REMOVING COCKPIT TMV AND INSPECTING BUTTERFLY VALVES FOR CONDITION, SPECIFICALLY FOR EVIDENCE OF CORROSION. REMOVED COCKPIT TMV AND INSPECTED VALVE AND FOUND ONE BUTTERLY VALVE METAL SEAL TO HAVE DETACHED. REMOVED AND REPLACED TMV IAW AMM 21-62-02/400 OPERATIONAL AND LEAK CHECK OF VALVE IAW AMM TASK 21-61-00-710-801-A, GOOD. REINSTALLED ACCESS PANELS PREVIOUSLY REMOVED.

Part: SKIN — DAMAGED (LE SLAT) · airframe 2,861 hrs · 2,233 cycles

BIRD STRIKE ON L/E STARBOARD WING. EVALUATED AND MAPPED DAMAGE ON RT OTBD L/E SENT DESCRIPTION OF DAMAGE TO CONTACT CENTER FOR ANALYSIS. REMOVED RT OTBD L/E IAW AMM TASK 57-40-00-000-801-A. REMOVED PICCOLO TUBE FROM DAMAGED L/E AND INSTALLED ON NEW RT OTBD L/E IAW AMM TASK 30-12-03-000/400-801-A. INSTALLED NEW RT OTBD L/E IAW AMM 57-40-00-400-801-A LOCATED DRILLED AND INSTALLED NEW SPLICE PLATE IAW SRM 51-40-02, 31, 40, 14 AMM 57-40-00-000-801-A. REF DWG NR 505-12662-005, REV A, OPS CHECK GOOD NO FURTHER DEFECTS NOTED.

Part: SLAT — DAMAGED (RT WING) · airframe 2,861 hrs · 2,233 cycles

BIRD STRIKE ON L/E STARBOARD WING.

Part: SWITCH — FAILED (BLEED SYS) · airframe 2,310 hrs · 1,800 cycles

BLEED LEAK 1, AMBER CAS MESSAGE ILLUMINATED, IN FLIGHT AT FL270. COMPLIED WITH QRH & QRC. SHUTDOWN NR 1 ENGINE & DIVERTED. R & R NR 1 ENGINE FWD BLEED LEAK THERMAL SWITCH. SYS OPS CHECKED GOOD IAW AMM 36-21-011400.

Part: SERVO — INOPERATIVE (AUTOPILOT) · airframe 269 hrs · 216 cycles

DURING CRUISE AT 40,000 FEET, AUTOPILOT FAIL, YAW DAMPER FAIL AND VENTRAL RUDDER FAIL CAS MESSAGES ALL DISPLAYED AT THE SAME TIME. ACFT IMMEDIATELY STARTED TO DUTCH ROLL, A EMERGENCY DECENT WAS STARTED AND AT THIS TIME THE DUTCH ROLL WAS EXCEEDING 30 DEGREES TO BOTH SIDES, IT APPEARED TO STAY THIS WAY UNTIL THE ACFT WAS APPROXIMATELY 25,000 FT, ABLE TO REGAIN THE YAW DAMPER, KEPT DECENT GOING TO 10,000, AND LEVELED OFF. LANDED WITHOUT FURTHER PROBLEMS. REPLACED AND CONFIGURED ROLL SERVO REFERENCING TASKS AMM 22-11-02-000-801A, 22-11-02-400-801A AND 22-11-02-470-801A . OPS TESTED SATISFACTORY. REPLACED AND CONFIGURED VENTRAL RUDDER SERVO REFERENCING TASKS AMM 22-11-11-000-801A, 22-11-11-400-801A AND 22-11-11-470-801A. OPS TESTED SATISFACTORY.

Part: INDICATOR — INOPERATIVE (LT MLG) · airframe 8,312 hrs · 7,111 cycles

LT MLG INDICATOR LIGHT INOP. USED NITROGEN TO BLOW GEAR DOWN.

Part: BULB — BURNED OUT (LT MLG INDICATOR) · airframe 8,312 hrs · 7,111 cycles

LT MLG INDICATOR LIGHT INOP. FOUND BULB IN INDICATOR TO BE BURNED OUT. REPLACED BULBS IN INDICATOR AS REQUIRED.

Part: SENSOR — INOPERATIVE (COCKPIT) · airframe 7,990 hrs · 6,815 cycles

DURING DESCENT, W/S AIR O HEAT ILLUMINATED THEN CYCLED OFF THEN ILLUMINATED AGAIN BUT CONTINUOUS. THE SWITCH WAS IN LOW AND COULD SMELL BURNING ODOR. REPLACE WINDSHIELD TEMPERATURE SENSOR AND TEMPERATURE BULB WITH NEW. OPS/LEAK CHECKS GOOD. DONE IN REF.

Part: BRAKE ASSY — LOCKED (MLG) · airframe 7,536 hrs · 6,436 cycles

CO-PILOTS BRAKES GRAB UNEVENLY DURING HIGH SPEED APPLICATION. 09-27-07 BLEED OUT BRAKES ON COPILOTS SIDE AND FOUND AIR, SUSPECTED AIR CAME FROM COPILOTS LT AND RT MASTER CYLINDERS PERFORMED IAW CE560 MM 32-42-01 AND 32-42-00.

Part: UNKNOWN — UNKNOWN (BRAKE SYSTEM) · airframe 7,006 hrs · 6,020 cycles

WHILE APPLYING BRAKE PRESSURE ON LANDING ROLLOUT THE BRAKE SYSTEM SURGES GIVING YOU THE SENSATION OF SLIPPING ON RUNWAY SURFACE.REMOVED ANTI-SKID TRANSDUCERS & INSPECTED FOR ANY UNUSUAL MOISTURE. FOUND NONE. TAXI (HIGH SPREAD) AIR CRAFT & APPLIED HEAVY BRAKING AIRCRAFT STOPPED STRAIGHT & ANTI SKID COVER BE FELT WORKING. OPS CHECKED GOOD. A SLIPPING SENSATION NEVER FELT WORK DONE IAW CE-560 AFM & CE-560 AMM CHAPTER 32-42-00.

Part: ACTUATOR — LEAKING (MLG) · airframe 6,939 hrs · 5,974 cycles

AT GEAR RETRACTION ON TAKEOFF, GEAR UNLOCK LIGHT (RED) AND HYD PRESS ON ILLUMINATED: PERFORMED K2 CHECKLIST, SPEEDBRAKE C/B + T/R C/B'S, NO CHANGE - GEAR C/B, GEAR UNLOCKED LIGHT WENT OUT, HYD PRESS ON STILL ILLUMINATED (GEAR EXTENDED, BOTH LIGHTS EXTINGUISHED). RETURNED TO FIELD. FOUND LT AND RT ACTUATORS LEAKING INTERNALLY. REMOVED AND REPLACED LT AND RT ACTUATORS IAW MM CH 32-31-04. OPS AND LEAK CHECKS GOOD. ADJUSTED CAMBER IAW MM CH 32-11-01 LT REMOVED P/N 1523100-7, S/N 402. INSTALLED P/N 1523100-7, S/N 534 RT REMOVED P/N 1523100-8, S/N 547. INSTALLED P/N 1523100-8, S/N 623.

Part: GYRO — INOPERATIVE (COCKPIT) · airframe 6,810 hrs · 5,863 cycles

ON TAKE-OFF ROLL HEADING MODE FAILED ON CAPT SIDE. HEADING MODE REMAINED INOPERATIVE BACK TO SERVICE CENTER RAMP. REMOVED AND REPLACED NR 1DB IAW MM 34-21-05. OPERATIONAL CHECKS GOOD.

Part: LINK — OUT OF ADJUST (MLG) · airframe 5,738 hrs · 4,966 cycles

AFTER GEAR RETRACTION NOTED EXCESSIVE AIR NOISE, EXTENDED GEAR, UPON RETRACTION HYD PRESS LIGHT REMAINED ON ALSO GEAR UNLOCK LIGHT STAYED ON. RE-EXTENDED GEAR AND HYD PRESS LIGHT WENT OUT AND GEAR UNLOCK LIGHT WENT OUT. ADJUSTED NOSE LANDING GEAR DOWN LINKAGE IAW CE560 M/M CHAP 32-21-01, LANDING GEAR EXTENDS AND RETRACTED TEN TIME WITH NO DEFAULT.

Part: ODOR — DETECTED (BATTERY BAY) · airframe 4,285 hrs · 3,826 cycles

ELECTRICAL ODOR ORIGINATING FROM CABIN AREA. SAME ODOR NOTICED IN BATTERY COMPARTMENT ON POST FLIGHT. - RAN AIRCRAFT AT CRUISE POWER FOR ONE HOUR, NO CIRCUIT BREAKERS POPPED, BATTERY TEMP STAYED AT 47 DEGREES F, TURNED A/C FREON UNIT ON , AVIONICS ON , AIRCRAFT SIMULATED CRUISE FLIGHT ON GROUND, DID NOT NOTICE ANY TYPE OF ELECTRICAL ODOR.