N390QS

Part: ENGINE — FAULTY (NR 2) · airframe 8,837 hrs · 6,913 cycles

UPON CLIMBING THROUGH APROX 2500', RECEIVED A E2 OIL LOW PRESSURE CAS MESSAGE. ADVISED NEEDED TO RETURN TO AIRPORT. ABOUT A MINUTE LATER DETECTED A BURNING ODOR WHICH WAS SHORTLY FOLLOWED BY SMOKE FILLING THE CABIN. DECLARED AN EMERGENCY & ADVISED RETURNING. RAN SMOKE EVACUATION QRC AFTER DONNING MASKS & GOGGLES ON A BASE LEG AND LANDING MOMENTARILY. CONFIGURED ACFT FOR LANDING & LANDED SAFELY. NOTICED A CONSIDERABLE AMOUNT OF SMOKE IN CABIN. FIRE DEPARTMENT USED HEAT SENSORS & DETECTED NO FIRES OR ANYTHING ABNORMAL. NOTED ON THE WALK AROUND THAT THERE WAS OIL DRIPPING OUT OF EXHAUST END OF THE ENG. CHECKED OIL DOOR & SAW THE OIL CAP WAS SECURED WITH VERY LITTLE TO NO OIL SHOWN IN SIGHT GAUGE. BORESCOPED RH ENGINE AND FOUND OIL AT FIRST STAGE SEAL INSIDE OF THE ENGINE. ENGINE REPLACEMENT PERFORMED BY EASW.

Part: BATTERY PACK — DEFECTIVE (ZONE 200) · airframe 8,673 hrs · 6,784 cycles

EMERGENCY LIGHTS ARE STAYING ILLUMINATED IN THE ARM POSITION. REPLACED BATTERIES. OPS CHECK GOOD. IAW AMM 33-52-01/400

Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 8,433 hrs · 6,602 cycles

DURING CRUISE THE EMERGENCY LIGHTS (WHILE IN THE ARM POSITION) PROCEEDED TO STAY ILLUMINATED AND THEN CONTINUOUSLY FLICKER. REMOVED AND REPLACED #1 FWD & #2 AFT EMERGENCY BATTERY REF EMS PHENOM 300 MM 33-52-01, OPS CHECKS GOOD AT THIS TIME NO DEFECTS NOTED

Part: PRIORITY VALVE — LEAKING (ZONE 700) · airframe 7,698 hrs · 6,047 cycles

EMERG BRAKE: USED EMERGENCY BRAKE BECAUSE HYDRAULIC SYSTEM FAILED BLOWING BOTH MAIN TIRES. PERFORMED REQUESTED ENGINE RUN AND IMMEDIATELY NOTICED HYDRAULIC FLUID LEAK FROM THE PRIORITY VALVE. REMOVED LEAKING PRIORITY VALVE. INSTALLED RECEIVED TESTED PRIORITY VALVE.

Part: HYDRAULIC SYSTEM — LOW PRESSURE · airframe 7,698 hrs · 6,047 cycles

MAIN HYDRAULICS: HYDRAULI LOW PRESSURE FAILURE- FAILED -PUSHER, BRAKES, GEAR, SPEEDBRAKE, RUDDER BOOSTER. ONCE AIRCRAFT WAS PLACED IN A HANGER TECHS NOTED HYDRAULIC FLUID LEAKAGE FROM BELLY AREA AFT OF LANDING GEAR. REACHED OUT TO MCC AND DISCUSSED FINDINGS. MCC ADVISED MOVING FORWARD WITH ENGINE RUNS TO DETERMINE THE SOURCE OF THE LEAK. PERFORMED REQUESTED ENGINE RUN AND IMMEDIATELY NOTICED HYDRAULIC FLUID LEAK FROM THE PRIORITY VALVE. AWAITED PART, REMOVED LEAKING PRIORITY VALVE. INSTALLED RECEIVED TESTED PRIORITY VALVE.

Part: ROD — OUT OF ADJUST (ZONE 800) · airframe 7,601 hrs · 5,965 cycles

MAIN CABIN DOOR HANDLE IS VERY STIFF & DIFFICULT TO CLOSE AND SECURE FROM THE INSIDE. ADDITIONALLY, WHEN HANDLE IS SECURED IN CLOSED POSITION THE STATUS PAGE SHOWS THE CABIN DOOR IS STILL OPEN. THERE IS NO GREEN FLAG PRESENT IN LOCK SIGHT WINDOW LOCATED ON BOTTOM STEP (UPPER RT WHEN DOOR IS CLOSED & VIEWED FROM INSIDE). REMOVED MAIN DOOR STEPS TO GAINED ACCESS TO INTERNAL DOOR MECHANISM. INSPECTED MAIN DOOR AND FOUND UPPER LOCK NOT CLOSING MICROSWITCH DUE UPPER ROD OUT OF ADJUSTMENT. PERFORMED ADJUSTMENT OF MAIN DOOR UPPER ROD & LUBED ALL MAIN CABIN DOOR LOCK PINS. PERFORMED SATISFACTORY OPS CHECK OF MAIN DOOR WITH DOOR CLOSED DOOR OPEN INDICATION GOES OUT ON STATUS PAGE & GREEN FLAG COME INTO VIEW ON SIGHT WINDOW. REINSTALLED CABIN DOOR STEPS IAW AMM 52-10-00.

Part: HANDLE — BINDING (ZONE 800) · airframe 7,601 hrs · 5,965 cycles

WHEN CLOSING MAIN CABIN DOOR FROM THE INSIDE THE RED HANDLE IS STICKING IN POSITION HALF WAY DOWN. IT TAKES A LOT OF FORCE TO MOVE THE HANDLE TO THE LOCKED POSITION ACCOMPLISHED PHENOM 300 AMM TASK 52-10-00-820-805-A -MAIN-DOOR LOCKING AND ACTUATING MECHANISM -ADJUSTMENT. OPS CHECK GOOD.

Part: BATTERY — DEFECTIVE (ZONE 100) · airframe 6,626 hrs · 5,209 cycles

CABIN EMERG LIGHT: CABIN EMER LIGHTS ILLUMINATED WITH THE EMER LIGHT SWITCH IN THE "ARMED" POSITION. CYCLED THE EMER LIGHT SWITCH OFF, THEN BACK TO ARM - CABIN EMER LIGHTS CONTINUED TO STAY ILLUMINATED. PERFORMED INERTIA SWITCH REACTIVATION WITH NO FIX. PERFORMED VISUAL CHECK ON EMER BA TT #1 AND 2 WITH NO DEFECTS NOTED. CHECKED CONNECTORS, NO DEFECTS NOTED. C/W CONT ACT CENTER RECOMMENDATIONS BY DISCONNECTING THE CONNECTOR ONE AT A TIME, ON EMERGENCY BATTERY 1 AND EMERGENCY BATTERY 2 AND PUT THE EMERGENCY SWITCH TO ARM. LIGHT FLICKERS WHEN EMERGENCY BATTERY 1 OR 2 CONNECTOR DISCONNECTED. PER CONTACT CENTER TROUBLESHOOTING GUIDE, BOTH BATTERY NEED CHARGE. COMPLYING WITH PHENOM 300 EMERGENCY BATTERY EXERCISE PROCEDURE TC-E5O-33-1OO1 REV O I6DEC2O22, BOTH EMERGENCY BATTERY DISCHARGE AND NEED TO BE RECHARGE PER TC STEP 7. PERFORMED PHENOM 300 EMERGENCY BATTERY EXERCISE PROCEDURE TC-E5O-33-IOOI, LIGHTS WORKS FOR COUPLE MINUTES AND THEN START BLINKING AGAIN. BOTH EMERGENCY BATTERIES ON ORDER. GAINED ACCESS TO REAR EMERGENCY BATTERY AND REMOVED AND REPLACED BATTERY PACK IAW EMB505 AMM 33-52-01. OPS CHECK OK. ALSO REMOVED AND REPLACED FWD EMERGENCY BATTERY PACK IAW AMM 33-52-01 AND SYSTEM OPS CHECK OK. ORIGINAL SUBMISSION DATE: 8-28-2023

Part: POWER SUPPLY — DEFECTIVE (EMERGENCY LIGHTS) · airframe 4,414 hrs · 3,517 cycles

CABIN EMERG LIGHT: IN CRUISE AT FL430 CABIN EMER LIGHTS FLICKERING ON AND OFF. CONTINUED THROUGH FLIGHT. GAINED ACCESS BY REMOVING CO-PILOTS SEAT AND CENTER FLOORBOARDS AFT OF PEDISTAL. REMOVED 3 EA VERTICAL PANELS IN AFT LAV. REMOVED THE FOLLOWING POWER SUPPLIES 1. FWD POWER SUPPLY P/N 6450LS S/N 001442 2. AFT POWERSUPPLY P/N 6450LS-00 S/N 000888 AND INSTALLED NEW POWER SUPPLIES. 1 FWD POWERSUPPLY P/N 6450LS-00 S/N 006611 2. AFT POWER SUPPLY P/N 6450LS-00 S/N 005509 AND INSTALLED ALL REMOVED ITEMS ALL WORK DONE I/A/W PHENOM 300 MM 33-52-00-710-801, 33-52-01-00-801, 33-52-00-400-801 OPS CHECK GOOD

Part: BALANCE WEIGHT — CORRODED (ZONE 300) · airframe 3,872 hrs · 3,089 cycles

DURING ACCOMPLISHMENT OF EMBRAER SERVICE BULLETIN 505-55-0004 REV 01 (DATED 06/24/2020) WE NOTED THE FOLLOWING MASS BALANCE WEIGHTS BELOW TOLERANCE AT LEFT AILERON: AILERON MASS WEIGHT PART NUMBER PE915109-L31 (1 EACH BELOW MINIMUM OF 1787G),WEIGHT HAS BEEN REPLACED WITH A NEW MASS WEIGHT AND THE AILERON BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED.THE LH AILERON WAS RE-IDENTIFIED TO PART NUMBER 505-14735-643 AS PER SERVICE BULLETIN INSTRUCTIONS. WE ALSO NOTED THE FOLLOWING RUDDER ADJUSTABLE MASS BALANCE WEIGHTS BELOW TOLERANCE: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L27 (5 EACH BELOW MINIMUM OF 455G), ALL WEIGHTS HAS BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE RUDDER BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED.THE RUDDER WAS RE-IDENTIFIED TO PART NUMBER 505-39061-619 AS PER SERVICE BULLETIN INSTRUCTIONS. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATOR’S GMM REQUIREMENTS

Part: BATTERY PACK — MALFUNCTIONED (EMERGENCY LIGHTS) · airframe 3,851 hrs · 3,072 cycles

CABIN EMERGENCY LIGHTS FLASHING IN FLIGHT WITH THE EMER LT SWITCH IN ARM. CORRECTIVE ACTION: REMOVED FWD EMER BATTERY P/N 6450LS-00, S/N 001098 AND AFT EMERGENCY BATTERY P/N 6450LS-00, S/N 000966 AND INSTALLED MODIFIED UNIT. OPERATIONS CHECKS GOOD.

Part: BATTERY — DEFECTIVE (EMERGENCY LIGHTS) · airframe 3,832 hrs · 3,062 cycles

CABIN EMERGENCY LIGHTS ILLUMINATED INTERMITTENTLY IN FLIGHT WITH LIGHT SWITCH IN "ARMED" POSITION. REMOVED AND REPLACED DEFECTIVE FWD AND AFT EMERGENCY BATTERIES, IAW EMB 24-65-03. OPERATONS CHECK GOOD.

Part: BEARING — WORN (LT ELEVATOR) · airframe 8,584 hrs · 7,041 cycles

ON CLIMB, FELT VIBRATION IN ALL CONTROLS AND COCKPIT SEATS. AT LEVEL OFF FELT VIBRATION SAME AS IN CLIMB BUT ALSO IN CABIN SEATS AND CABIN SIDEWALLS LT SIDE REPORTED WORSE THAN RT SIDE, DESCENT FELT VIBRATIONS ALSO. FOUND RUDDER TRIM AND LT ELEVATOR TRIM TABS WITH EXCESSIVE PLAY REMOVED AND REPLACED BRGS AND HARDWARE. OPS CHECK GOOD. IAW MM 27-11-00, 27-21-00. ALSO JACKED ACFT AND RETRACTED GEAR, VERIFIED PROPER RIG OF ALL GEAR DOORS. OPEN RT NOSE GEAR DOOR. INSP CHECK GOOD. CLOSED NLG DOOR. DOWN JACKED ACFT. INSPECTED AIRFRAME FOR POSSIBLE CAUSE OF VIBE. FOUND RUDDER TRIM TAB LT ELEVATOR TRIM TABS WITH EXCESS FREE PLAY. NEED TO REPLACE THE LT ELEV TAB HORN BRGS AND HARDWARE. ALL WORK PERFORMED IAW MM 27-11- AND 27-21-00.

Part: UNKNOWN — VIBRATION

ON CLIMB FELT VIBRATION IN ALL CONTROLS AND COCKPIT SEATS. (A)

Part: CONNECTOR — BROKEN (ELECTRICAL) · airframe 8,178 hrs · 6,695 cycles

WHILE AT CRUISE ALT 32000 WITH 28 MIN INTO THE FLIGHT, ACFT FAIL LIGHT CAME ON WITH MASTER WARNING. ACFT FAIL LIGHT STAYED ON UNTIL WE RESET MASTER WARNING AFTER 5 MIN. DURING THIS TIME VOLTS SHOWED 28 AND GENS SHOW 50 AMPS EACH AND WERE STEADY. INVERTERS SHOWED GOOD. M2B- FOUND CONNECTOR PN 383 OF NOSE AVIONICS J-BOX WITH BROKEN THUMBSCREEN CAUSING LOOSE CONNECTION REPLACED THUMBSCREEN WITH NEW, OPS CHECK NORMAL IAW MM 20-21-03 AND 560 WDM 24-20-01

Part: BRAKE ASSY — WEAK (COPILOT) · airframe 7,577 hrs · 6,193 cycles

COPILOTS BRAKES BEING WEAK, SOFT OR SPONGY. [SUP 04-27-07] TAXIED ACFT AND FOUND EXCESSIVE TRAVEL ON COPILOT'S LEFT PEDAL. BRAKE SYSTEM BLED, AIR BUBBLES SEEN WHEN LEFT BRAKE BLED. TAXIED ACFT AND BRAKES CHECK GOOD. COPILOT PEDAL REQUIRE EQUAL FORCE FOR STOPPING. OPS & LEAK CHECK GOOD ON BRAKES.

Part: BRAKE ASSY — LEAKING (LEFT) · airframe 7,567 hrs · 6,184 cycles

CO-PILOTS BRAKES ARE MUSHY, ESPECIALLY THE LT. FLUID NOTED ON LT BRAKE ASSEMBLY. REMOVED PILOTS LT MASTER CYLINDER & INSTALLED IN CO-PILOTS LT POSITION. CO-PILOTS LT MASTER CYLINDER REMOVED FROM SERVICE. INSTALLED OVERHAULED MASTER CYLINDER IN PILOTS LT POSITION. REMOVED & REPLACED CO-PILOTS RT MASTER CYLINDER WITH OVERHAULED UNIT. REPLACED PILOTS LT CYLINDER FITTINGS & INLET HOSE WITH NEW, BLED SYSTEM, OPS & LEAK CHECKED GOOD, TAXI CHECK PERFORMED, OPS -CHECK OF BRAKE SYSTEM GOOD, NO DEFECTS NOTED.

Part: BRAKE ASSY — MALFUNCTIONED (MLG) · airframe 7,527 hrs · 6,150 cycles

BRAKES ON SIC SIDE NEED TO BE PUMPED TO BE EFFECTIVE AFTER LANDING. BLED BRAKE SYSTEM ON SIC SIDE IAW CH 32-42-00 OF CE 560 M.M.

Part: RUDDER — UNKNOWN (EMPENNAGE) · airframe 7,146 hrs · 5,867 cycles

RUDDER TRIM REQUIRES EXCESSIVE TRIM TO RIGHT & AILERON TRIM REQUIRES EXCESSIVE TRIM (WANTS TO ROLL LEFT). REPLACED RUDDER WITH SERVICEABLE RUDDER FROM AIRCRAFT S/N 560-0437 IAW CE560 MM CHAP 27-21-01 FOR CONTINUED SERVICE C/W TRAVEL CHECKS (GOOD).

Part: UNKNOWN — UNKNOWN (FLT CONTROL) · airframe 7,145 hrs · 5,866 cycles

TO MAINTAIN LEVEL FLIGHT AT 5000 FT MSL, 240KIAS, A/C NEEDS 1/2 OF RIGHT RUDDER TRIM TRAVEL TO CENTER BALL AND 3 ROLLS OF AILERON TRIM. A/C ROLLS LEFT WITH TRIMS CENTERED (WILL ROLL INVERTED IF NOT HELD WITH 25-30 LBS OF FORCE. C/W RIG/TRAVEL CHECKS ON ALL PRIMARY/SECONDARY CONTROL SURFACES. ALL CHECKS GOOD AT THIS TIME. CHECKED GEAR DOOR FOR FIT, CHECKS GOOD. REMOVED RUDDER AND CHECKED BALANCE. BALANCE CHECK GOOD. REINSTALLED RUDDER. ALL WORK DONE IAW CE560 MM 27-11-00, 27-31-00, 27-21-00 AND 27-51-00.

Part: UNKNOWN — UNKNOWN (BRAKE PEDAL) · airframe 7,705 hrs · 6,303 cycles

ON LANDING CAPTAIN'S BRAKE PEDALS WENT TO FLOOR WITH MEDIUM EFFECTIVENESS. [07-10-07] MANUALLY BLED BRAKES AND FOUND AIR IN LT AND RT BRAKES. PURGED SYSTEM OF AIR, C/W TAXI CHECK. TAXI CHECK GOOD AT THIS TIME. NO LEAKS NOTED AT THIS TIME. BRAKE BLEED I/A/W CESSNA 560 M/M 32-42-00.

Part: MASTER CYLINDER — LEAKING (BRAKES) · airframe 6,371 hrs · 5,226 cycles

ANTI-SKID ANNUNCIATOR ILLUMINATED AND WILL NOT EXTINGUISH AFTER CYCLING THE ANTI-SKID SWITCH AND CIRCUIT BREAKER. BRAKES WORK AT SLOW TAXI SPEEDS BUT ARE NEARLY INOP AT HIGHER SPEEDS. REPLACED CO-PILOT RT BRAKE MASTER CYLINDER, ANTI-SKID SYSTEM FAULT MONITOR AND LT SKID TRANSDUCER CANNON PLUG. OPS CHECKED GOOD IAW CESSNA 560 MM 32-42-00

Part: ENGINE — MALFUNCTIONED (LEFT) · airframe 6,360 hrs · 5,218 cycles

LEFT ENGINE FAILED AFTER APPROXIMATELY 2-3 MINUTES OF GROUND RUN. PERFORMED ENGINE START UP AND GROUND RAN ACFT FOR 10 MIN. REPEATING PROCEDURE 3 TIMES. DURING RUNS SELECTED VARIOUS MODES OF OPS SUCH AS LT & RT BOOST PUMPS ON/OFF LOW & HIGH GRD IDLE. CABIN PRESS AND BLEED AIR ON/OFF OBSERVED ENG PARAMETER, INDICATORS GAUGES AND ANNUNCIATIONS. NO FAULTS NOTED, NO FAULTS OR ABNORMALITIES FOUND AT THIS TIMEWORK IAW 560 PILOT'S OP MANUAL.

Part: INDICATOR — MALFUNCTIONED (TRIM) · airframe 5,153 hrs · 4,201 cycles

DURING TAKEOFF ROLL PILOT EXPERIENCED EXCESSIVE BACK PRESSURE ON THE CONTROL COLUMN, TOOK APPROX 60 LBS OF FORCE TO NEUTRALIZE CONTROL COLUMN, TRIM INDICATOR WAS IN T/O RANGE, TAKEOFF ABORTED. INSPECTED ELEVATOR AND ELEVATOR TRIM SYSTEM, FOUND ELEVATOR TRIM WHEEL INDICATOR AT TAKEOFF POSITION BUT ELEVATOR TRIM AT FULL NOSE-UP POSITION. RE-INSTALLED TRIM INDICATOR AND WHEEL TO ONE CORRECT READINGS. CHECK ELEVATOR AND TRIM UP / DOWN DEGREES OF TRAVEL, NO DEFECTS NOTED, TRIM WHEEL OP'S CHECK GOOD. WORK PERFORMED IAW CESSNA CE-560 MAINTENANCE MANUAL CHAPTER 27-31-05.