EXECUTIVE FLIGHT SERVICES, LLC

Operated by Executive Flight Services LLC (per NTSB report)

Operated by Executive Flight Services, Inc (per NTSB report)

FOUND CRACK ON LH AND RH NOSE OMEGA BEAM FORWARD SUPPORT BRACKET

FOUND CRACK ON LH AND RH NOSE OMEGA BEAM FORWARD SUPPORT BRACKET

DUAL GENERATOR FAILURE AT FL 430. EMERGENCY DECENT, AIRCRAFT WENT INTO ELECTRICAL EMERGENCY. PRESSURIZATION LOSS, O2 MASKS DEPLOYED. AIRCRAFT LANDED AND EMERGENCY BRAKING WAS USED, WHICH RESULTED IN THE TIRES FLAT SPOTTED INTO THE WHEEL. MX DOWNLOADED CMC AND CVDR/FDR INFO FOR EMBRAER. EMBRAER WAS UNABLE TO DETERMINE A CAUSE. EMBREAR RESPONSE "DUAL GENERATOR OFF-BUS IS MOSTLY RELATED TO ONE FAILED GENERATOR AND OPENS THE OPPOSITE SIDE AS A PROTECTION MODE TRIGGERED BY GCUS." PILOT UNABLE TO IDETIFY WHICH STARTED FAILED FIRST. MX INSPECTED BOTH STARTER GENEREATORS AND PREFORMED SATISFACTORY OPERATIONAL CHECKS OF THE STARTER GENERATORS AND DC OPERATION. AIRCRAFT IS TO BE FERRIED TO EMBRAER AT MESA AZ FOR FURTHER ANALYSIS.

LH WINDSHIELD CRACKED IN CLIMB AT FL 270

LH WINDSHIELD CRACKED IN CLIMB AT FL 270

NO LANDING GEAR INDICATION WHEN SELECT LEVER SELECTED DOWN.

ECS VALVE 1 FAIL - RESET ONCE ON GROUND WITH POWER CAME BACK 2 MIN LATER

ON POWER UP, ECS 1 VALVE FAIL CAS. POWER CYCLE AND ENGINE RUN MADE NO DIFFERENCE

GEN 1 FLUCTUATING VOLTAGE.(28.6-25.1 APPX.) DURING CRUISE FLIGHT. OIL LEAKING FROM GEN OUTLET.

AFTER LANDING, BRAKE FAIL CAS MESSAGE AND BRAKES INEFFECTIVE. EMERGENCY BRAKE USED TO STOP.

BLEED 1 FAIL IN FLIGHT

FLAP FAIL CASS ON DESCENT TO ECP. DECLARED EMERGENCY AND LANDED WITH FLAP UP CONDITION. NO INCIDENT ON LANDING. CMC SHOWED FAILURE OF FLAP PDU. REPLACED WITH SERVICEABLE UNIT. OPERATIONAL CHECK SATISFACTORY.

AT ALTITUDE BLEED 1 CYCLES BETWEEN OPEN AND CLOSE IN AUTO

VISUAL INSPECTION REVEALS FOULING CONDITION EXISTS WHEN STEERING DAMPER IN FRONT OF PILOTS RUDDER PEDALS DURING OVERSTEERING EXTENDS FAR ENOUGH TO STRIKE AND EVENTUALLY CATCH AND BEND WIRING BRACKET AND CLAMP INBOARD AND FOUL THE WIRE BUNDLE.

VISUAL INSPECTION REVEALS FOULING CONDITION EXISTS WHEN STEERING DAMPER IN FRONT OF PILOTS RUDDER PEDALS DURING OVERSTEERING EXTENDS FAR ENOUGH TO STRIKE AND EVENTUALLY CATCH AND BEND WIRING BRACKET AND CLAMP INBOARD AND FOUL THE WIRE BUNDLE.

GEN 1 FAIL CAS

WE EXPERIENCED MULTIPLE COCKPIT EFFECTS INCLUDING LOSS OF BATT 1 VOLTAGE INDICATION, SWPS FAIL, PUSHER TEST FAIL, ENGINE NO DISPATCH, SAT, TAT, ISA, SHOWING RED X’S, ETC. TROUBLESHOOTING THIS ISSUE LED US TO A DAMAGED WIRE BUNDLE FORWARD OF THE PILOTS LEFT RUDDER PEDAL. MULTIPLE DAMAGED WIRES AND WERE THE CAUSE OF THE INDICATION LOSSES. SHORTED WIRING ALSO CAUSED THE STICK PUSHER SOLENOID TO FAIL AND REQUIRE REPLACEMENT. FURTHER INSPECTION TO DETERMINE HOW THIS BRACKET WAS FOULED, WE DISCOVERED THAT THE DAMPENER FOR OVERSTEERING EXTENDS FAR ENOUGH TO STRIKE AND EVENTUALLY CATCH AND BEND THIS WIRING BRACKET AND CLAMP INBOARD AND FOUL THE WIRE BUNDLE. THIS ISSUE HAS BEEN REPORTED TO EMBRAER AND IS BEING HANDLED UNDER EMBRAER CASE: EEJ-04457794. WE HAVE STARTED INSPECTING OUR OTHER EMBRAER 300 AND HAVE FOUND TWO OTHER AIRCRAFT AFFECTED SN'S 50500368, 50500513.

ECS 1 VALVE FAIL CAS

INTERMITTENT ECS2 FAIL CAS

#1 ENGINE VIBRATION REPORTED ON START UP BY PILOT. AFTER REMOVAL - MECHANIC REPORTED SUSPECT SHAFT SIDE PLAY

BRK FAIL" CAS MESSAGE. BRAKES FAILED WHILE AIRCRAFT WAS IN MOTION WHILE ATTEMPTING TO TAXI. EMERGENCY BRAKE WORKED.

BLEED 2 OVERPRESSURE FOLLOWED BY BLEED 2 FAIL.

#2 ENGINE WOULD NOT ROTATE UPON ATTEMPTED ENGINE START.

EXCESSIVE DUST FOUND ON COWLING DURING INSPECTION

ECS 1 FAIL CAS

BLEED 2 OVERPRESSURE FOLLOWED BY BLEED 2 FAIL

AFTER DEPARTING MMSL, ON CLIMB OUT PILOT EXPERIENCED SLIGHT VIBRATION. PULLING #1 THROTTLE BACK REDUCED VIBRATION. BATTERY 1 VOLTAGE WENT TO YELLOW, THEN BACK TO GREEN ELECTRICAL SYNOPTIC AMPS/VOLTS WERE FLUCTUATING. SHORTLY AFTER THE "GEN 1 OFF BUS" CAME UP. ENGINE WAS SHUT DOWN IN FLIGHT. AIRCRAFT DIVERTED TO MMSD.

ECS VALVE 2 FAIL CAS

BLEED 1 FAIL CAS

ECS 2 VALVE FAIL CAS CLIMBING THROUGH FL300

ON TAXI OUT. ECS 2 FAIL CAS. ECS DISPLAY SHOWED RED X ON ECS VALVE 2.

FLAP FAIL ON AVIONICS POWER UP.

#2 FSOV FAIL

FLAP FAIL MESSAGE YELLOW BOX ON FLAP INDICATOR ON POWER UP.

ECS 1 OFF IN FLIGHT CASS

BLEED 2 OVERPRESSURE FOLLOWED BY A BLEED 2 FAIL

ON APPROACH, FLAP FAIL CASS RECEIVED WHEN SELECTING FLAPS FULL. RECEIVED GREEN "S" INDICATION WHEN MOVED TO "3"POSITION.

COCKPIT AIR CONSTANTLY DEMANDING HIGH VOLUME. DOES NOT MODULATE TO LOWER AIRFLOW SETTINGS.

EMERGENCY LIGHTS REMAIN ON IN ARM POSTION - INTERMITTENT FLICKERING

AFTER ENGINE START, FLAP FAIL CAS MESSAGE WITH FLAP HANDLE IN POSITION ). FLAP HANDLE IN POSITION 1 CONTINUED WITH YELLOW FLAP INDICATIONS AND CAS MESSAGE. RETURN HANDLE TO POSITION 0 MADE CAS MESSAGE DISAPPEAR AND GREEN FLAP 0 INDICATIONS APPEARED.

FAILED REDUCED FREQUENCY CAPACITY CHECK. (3 MONTH INTERVAL)

VIBRATION REPORTED BY PILOT

NO ROTATION UPON ENGINE START ATTEMPT

AFTER START; GEN 1 OFF BUS. POWERED DOWN RESTARTED AND RECEIVED ENGINE 1 CTRL FAULT

BLEED 2 PRSOV FAIL

GEN 1 OFF BUS. POWERED DOWN, RESTARTED AND RECEIVED ENG CTRL FAULT

BLEED 1 OVER PSI, FOLLOWED BY BLEED1 FAIL IN FLIGHT

GEN 1 OFF BUS CAS.

ON APPROACH, PILOTS RECEIVED A BRAKE FAIL CASS MESSAGE. PILOT DECLARED EMERGENCY AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE LEFT BRAKE CONTROL VALVE FAILED AND REPLACED.

ECS 2 FAIL CAS.