N302QS

Part: SKIN — SCRATCHED · airframe 9,848 hrs · 7,757 cycles

BLENDED SCRATCHES ON THE LT & RT LEADING EDGES, PERFORMED NDT AND PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. VERIFIED NO BLENDS EXCEEDED THICKNESS MATERIAL LOSS EXCEEDING 5% AND POLISHED PER REQUEST FOR TECHNICAL SERVICES REPORT.

Part: BATTERY PACK — FAULTED (ZONE 200) · airframe 9,610 hrs · 7,554 cycles

FORWARD CABIN EMERGENCY LIGHTS COME ON FOR A FEW MINUTES THEN GO OUT FOR AWHILE AND THEN COME BACK ON FOR A FEW MINUTES, REPEATEDLY. REMOVED BOTH EMERGENCY BATTERY PACKS AND INSTALL OPERATOR SUPPLIED BATTERY PACKS PER AMM 33-52-01. ALL OPS CHECKS GOOD, NO FURTHER DEFECTS NOTED.

Part: SWITCH — FAULTED (EMERGENCY LIGHTS) · airframe 8,366 hrs · 6,575 cycles

EMERGENCY SWITCH WAS IN THE ARMED POSITION. EMERGENCY FLOOR LIGHTS ELUMINATED WITH NO CAUSE. WE LEFT THEM ON AND THEY BEGAN BLINKING. WE SWITCHED THEM TO OFF AND THE EMER LT NOT ARM ELUMINATED FOR THE DURATION OF FLIGHT. REMOVED FAILED IMPACT SWITCH P/N 7212-4-000 S/N 0004. INSTALLED A NEW CUSTOMER SUPPUED SWITCH P/N 7212-4-000 S/N 0374. VISUAL AND OPERATIONAL TESTS SATISFACTORY. ALL WORK IAW EMB5500 MM:33-52-17.

Part: GDS — FAULTY (UNKNOWN) · airframe 8,214 hrs · 6,461 cycles

REMOVED FAILED GDS 1 AND INSTALLED A REPAIRED GSD 41, WORK DONE IAW AMM 31-41-01. PERFORMED GSD 1 SOFTWARE/CONFIGURATION UPLOADING IAW AMM 31-41-01. PERFORMED OPS TEST OF GDS 1, SUCCESSFUL IAW AMM 31-41-01.

Part: BATTERY — DEFECTIVE (UNKNOWN) · airframe 8,163 hrs · 6,427 cycles

IN FLIGHT, THE CABIN EMERGENCY LIGHTS WERE CONTINUING TO PULSE. REMOVED AND REPLACED EMERGENCY BATTERY. IAW TASK 33-52-01-400-801-A

Part: LIGHT — DEFECTIVE (ZONE 200) · airframe 7,612 hrs · 5,991 cycles

CABIN EMERG LIGHT: FORWARD CEILING EMERGENCY LIGHT BY MAIN CABIN DOOR DOES NOT ILLUMINATE WHEN EMER LT SWITCH SELECTED TO ON. BOTH THE MIDDLE AND AFT ILLUMINATE NORMALLY. POWERED UP AND ARMED EMER LIGHTING SYSTEM. VERIFIED OVERHEAD CEILING EMER LIGHTS OVER MED DO NOT ILLUMINATE. REMOVED LIGHT ASSMEBLY TO GAIN ACCESS TO P/N AND NOTIFIED MCC TO PLACE ON ORDER, LIGHT ASSY P/N 5336-00. POO. (KA, 05/29/23) RECEIVED LIGHT ASSEMBLY P/N 5336-00 AND INSTALLED REFERENCING EMREAR EMB505S MM TASK 33-26-01-400-801-A.PERFORMED AND OPERATIONAL CECK NOTING NO DEFECTS AT THIS TIME

Part: NONE — NONE · airframe 6,651 hrs · 5,240 cycles

CABIN EMERG LIGHT: IN FLIGHT WITH EMER LIGHT ARMED, EMERGENCY LIGHTS IN CABIN WERE FLASHING.///SIGN-OFF///PREFORMED TROUBLESHOOTING IAW EMBRAER SERVICE LETTER NO. 505-33-0005. AFTER CHARGING BATTERIES PER STEP 3. PREFORMED OPS CHECK OF EMERGENCY LIGHT IAE PHENOM 300 AMM 33-52-00. ALL CHECKS GOOD.

Part: BALANCE WEIGHT — CORRODED (STAB) · airframe 5,889 hrs · 4,655 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 ELEVATOR: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (7 EACH BELOW MINIMUM OF 84G); HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G); MASS WEIGHT INBOARD PART NUMBER PE915109-L40 (1 EACH BELOW MINIMUM OF 2809G) MASS WEIGHT OUTBOARD PART NUMBER PE915109-L41 (1 EACH BELOW MINIMUM OF 2049G). ALL WEIGHTS HAS BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED. THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11094-615, AS PER SERVICE BULLETIN INSTRUCTIONS. WE ALSO NOTED THE FOLLOWING RIGHT ELEVATOR MASS BALANCE WEIGHTS BELOW TOLERANCE: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (6 EACH BELOW MINIMUM OF 84G); HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G); MASS WEIGHT OUTBOARD PART NUMBER PE915109-L41 (1 EACH BELOW MINIMUM OF 2049G). ALL WEIGHTS HAS BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED. THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11094-616, AS PER SERVICE BULLETIN INSTRUCTIONS. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATOR’S GMM REQUIREMENTS

Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 5,685 hrs · 4,491 cycles

DISCREPANCY: AIRCRAFT CREW REPORTED "ON GROUND JUST BEFORE ENGINE START, GROUND POWER UNIT CONNECTED AND ON WITH EMERGENCY LIGHT SWITCH IN "ARM" POSITION", THE EMERGENCY LIGHTS STAY ON AND THE YELLOW "EMER LT NOT ARM" AND ANNUNCIATOR ILLUMINATES. PERFORMED TROUBLESHOOTING BASED ON THE EMBRAER PHENOM 300 FIM TASK CHAPTER 33-50-00-801-801-A AND FOUND #1 EMERGENCY BATTERY LIGHTS (FORWARD) FAULTY. PERFORMED REPLACEMENT #1 (FORWARD) EMERGENCY LIGHT BATTERY IN ACCORDANCE WITH PHENOM 300 AMM CHAPTER 33-52-01. PERFORMED OPERATIONAL TEST OF EMERGENCY LIGHT BATTERY IN ACCORDANCE WITH PHENOM 300 AMM CHAPTER #33-52-00. NO DEFECTS NOTED. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATOR'S GMM REQUIREMENTS.

Part: SENSOR — FAILED (BLEED TEMP) · airframe 5,375 hrs · 4,251 cycles

DURING CLIMBOUT CRUISE AND DESCENT EXPERIENCED WHITE SHED BUS 1&2 OFF INTERMITTENTLY AND AN BLEED 1 FX THAT WENT AWAY VIA THE CHECKLIST. BELOW 10,000 FT. AMBER CONTOL FX, A/P FX SWPS FAULT AND SEPS A/ I, ALONG WITH YD FX AND A/P FX. ///SIGN-OFF///THE BLEED SYSTEM WAS AN ISOLATED EVENT AND THE RECOMMENDATION IS TO FOLLOW SL505-36-0003-REV.02 - PNEUMATIC- BLEED 1 (2) FAIL DUE TO BLEED TEMPERATURE SENSOR. ON BLEED ONE FAILURE WE PERFORM GROUND RUN OF BOTH ENGINE DID OPS CHECK OF THE BLEED AIR SYSTEM IAW EMS 505S AMM 36-00-00-710-801-A/500 OPS CHECKED GOOD NO DEFECTS NOTED. NEXT WE C/W SL505-36-0003 REV.02 AND FOUND NO DEFECTS AND IS FOUND TO BE TRANSITORY CONDITION. NO FUTHER ACTION AT THIS TIME. DURING ENGINE GROUND RUN AND LEAK CHECK OF FOUND FAN VALVE TO PRECOOLER LAIR LINE LEAKING FROM FLANGE , FLANGE SEPERATED FROM FIBERGLASS TUBE AT FAN VALVE. ORDERED NEW TUBE AND RECEIVED IT REMOVE OLD TUBE AND INSTALLED NEW TUBE LAW EMB505S AMM 36-11-02 OPS CHECKED AND LEAK CHECKED GOOD.

Part: CONTROL UNIT — FAILED (TE FLAPS) · airframe 768 hrs · 570 cycles

SHORTLY AFTER LEVELING AT FL430, SWPS FAULT AMBER CAS CAME ON ALONG WITH THE WHITE, SPOILER FAULT MESSAGE. THERE WERE YELLOW X'S IN THE FLAP INDICATOR, PITCH TRIM INDICATOR & ON THE STBY SYS THE YELLOW LETTERS, SSEC, IN LOWER LT & YELLOW X JUST LT OF THE ALTITUDE INDICATOR WERE PRESENT. DESCENDED TO FL 250 & CHECKED PITCH TRIM OPERATION WHICH TESTED NORMAL BUT THE X STAYED SO WE COULDN'T READ THE TRIM SETTING. ON APPROACH, EXTENDED FLAPS TO 1 THEN 2 WITH NO RESULT. A VISUAL CHECK CONFIRMED THE FLAPS DID NOT EXTEND. REMOVED NR 1 FCE & INSTALLED A TESTED FCE. COMPLETED FLAP RIGGING & OPS CHECKS. CHECKED SATISFACTORY IAW MM 27-03-01.

Part: DISPLAY — FAILED (COCKPIT) · airframe 53 hrs · 32 cycles

AFTER DEPARTURE, PFD 1 FAILED AND REVERTED. MFD FAILED AND REVERTED. COMM 1 FAILED. TXPDR 1 FAILED. SPLIT SCREEN JEPP CHARTS ON PFD FAILED. APPROX A DOZEN CAS MESSAGES DISPLAYED. PFD 1 COMM 1 CAME BACK ONLINE. THE CAS MESSAGES FOR SWPS FAULT(YELLOW), XPDR 1 FAIL(WHITE) AND SWPS ICE SPEED(WHITE) REMAINED ON. AFTER FOLLOWING THE QRH PROCEDURE FOR THE XPDR 1 FAIL, XPDR 1 RETURNED TO NORMAL. THE QRH PROCEDURES WERE COMPLETED FOR THE SWPS FAULT AND IT AND THE SWPS ICE SPEED REMAINED ON THROUGH LANDING. FAULT CODES 273-014-00 AND 273-016-00 FOR SWPS FAULT AND SWPS ICE SPEED.

Part: SEAL — FAILED (DOOR) · airframe 10,831 hrs · 8,911 cycles

AT FLT LEVEL 390, A SUDDEN, EXTREMELY LOUD SQUEALING NOISE FILLED CABIN, NO SECONDARY INDICATIONS OF A PRESSURE ISSUE AT THE TIME. STARTED A RAPID DESCENT AS A PRECAUTION, NOISE DID NOT DISSIPATE UNTIL BELOW 6000 FT WHEN CABIN & AIR PRESSURE EQUALIZED. COMPLETED CONTROLLER TO PNEUMATIC RELAY CONNECTION LEAKAGE TEST & VACUUM & PNEUMATIC RELAY TO OUTFLOW VALVES PNEMATIC CONNECTION LEAK TEST (CHECK 1 AND 2). BOTH CHECKS SATISFACTORY. COMPLETED A CABIN LEAK TEST & SECONDARY DOOR SEAL TEST. SECONDARY DOOR SEAL FAILED. FOUND SEAL BLOWING OUT ON LOWER DOOR. ADJUSTED DOOR/SECONDARY SEAL IN REF TO THE MM 52-10-01. COMPLETED A CABIN LEAK CHECK & SECONDARY DOOR SEAL. BOTH PASSED IAW THE MM 21-31-00.

Part: UNKNOWN — ODOR (CABIN) · airframe 10,688 hrs · 8,788 cycles

NOTED FAINT ELECT/ BURNED INSULATION TYPE ODOR IN FLIGHT. NO SMOKE. COULD NOT IDENTIFY THE SOURCE. PRECAUTIONARY LANDING MADE. INSPECTED ACFT AND PERFORMED NUMEROUS ENG RUNS LETTING THE HEAT BLOW FULL HOT EACH TIME. COULD NOT DUPLICATE ANY ODOR OR BURNED SMELL. REMOVED AND INSPECTED WATER SEPERATOR COALESCER WITH NO DEFECTS NOTED. REINSTALLED COALESCER AS REQUIRED. CANNOT DUPLICATE SQK AT THIS TIME.

Part: FLOW DIVIDER — MISRIGGED (RT ENGINE) · airframe 10,013 hrs · 8,223 cycles

RT ENGINE QUIT ON LANDING ROLL OUT. ENGINE QUIT WHEN RT THROTTLE WAS BROUGHT TO IDLE. RT THROTTLE SEEMS TO HAVE AN EXCESSIVE AMOUNT OF SLOP WHEN BROUGHT BACK TO IDLE THRUST. VERIFIED DISCREPANCY, FOUND RT ENGINE CONTROLS AT FCU AND FUEL FLOW DIVIDER IMPROPERLY RIGGED. FOUND FCU CONTROL LEVER MIS CLOCKED. PERFORMED ONE COMPLETE RIGGING OF FCU AND FFD AS REQUIRED. PERFORMED ENG RUN AND RAPID ACCELERATION, ALL CHECK SATISFACTORY. ALL DONE IAW MM 76-11-00, 71-00-00. REPLACED OIL FILTER PN 3119604-01 AND FILTER ELEMENT PN 3059779-01.

Part: ENGINE — MALFUNCTIONED (RIGHT) · airframe 10,013 hrs · 8,223 cycles

RIGHT ENGINE QUIT ON LANDING ROLL OUT.

Part: ENGINE — SHUTDOWN (RIGHT) · airframe 10,012 hrs · 8,222 cycles

RIGHT ENGINE QUIT ON LANDING APPROACH ABOUT 100 AGL THROTTLES AT IDLE.

Part: ENGINE — UNKNOWN (RIGHT) · airframe 10,012 hrs · 8,222 cycles

RT ENGINE QUIT ON LANDING APPROACH ABOUT 100 AGL THROTTLES IDLE. REMOVED LT/RT ENG LWR COWLS FOR ACCESS. RE-RIGGED RT FDV TO FUEL CONTROL RD. ADJUSTED RT THROTTLE CABLE. INSPECTED LT FDV TO FUEL CONTROL RIGGING AND THROTTLE RIGGING AT FCU NO DEFECTS NOTED. RAN BOTH ENGINES. ADJUSTED LT HIGH AND LOW IDLES. ADJUSTED RT LOW IDLE. C/W POWER CK, IDLE CK AND SLAM CK. C/W 5 PT RUNS, ACCELL AND DECEL CK'S. C/W 85-65 PERCENT SWITCH OPS TEST. C/W CHECKLIST PROVIDED. C/W THROTTLE SPLIT OPS TEST. ALL OPS CK'S GOOD IAW. MM CH 71-01-02 COWLED ENGINES.

Part: RETAINER — MISSING (BRAKES) · airframe 9,960 hrs · 8,176 cycles

RT SEAT BRAKES NOT OPERATING PROPERLY. DURING TAXI, YOU MUST GO VERY FAR ON THE BRAKES TO GET ANY RESISTANCE. NORMAL BRAKING ON LT SEAT SIDE. NO FLUID NOTED UNDER PEDALS OR WHEELS. VERIFIED DISCREPANCY TROUBLESHOT AND FOUND RT RUDDER TORQUE TUBE SUPPORT ASSY MISSING FASTENERS AT LOWER RT INSTRUMENT PANEL SUPPORT ANGLE REPLACED MISSING SCREWS AND 1 SECURED RUDDER TORQUE TUBE SUPPORT ASSY BLED THE ANTI SKID BRAKE SYS IAW EO M344-08-10 OPS CHECKED GOOD LEAK CHECKED GOOD CH 32-41-01.

Part: BRAKE SYS — CONTAMINATED · airframe 9,911 hrs · 8,141 cycles

COPILOT RT BRAKE PEDAL IS LESS EFFECTIVE THEN THE LT PEDAL. MORE TRAVEL IS NEEDED TO PRODUCE BRAKE PRESSURE. PERFORMED VISUAL INSP, CHECKING BRAKE LINES IN COCKPIT, CHECKED MASTER CYLINDER FLEXIBLES AND BRAKE ASSY FOR CONTAMINATION OR POSSIBLE FLUID LEAK IAW TASK CARD TC 560-32-080602. PERFORMED BRAKE BLEEDING PROCEDURE IAW MM CH 32-42. OPS CHECK GOOD. TAXI CHECK GOOD.

Part: STARTER GEN — MALFUNCTIONED (LT ENGINE)

STARTER DISENGAGE PROBLEM - ABORTED LT ENG START WHEN N2 AT 25% AND NO N1. ENG APPEARED TO SHUTDOWN NORMALLY. F/O CHECKED, ENG WAS STILL RUNNING AND SMOKE WAS COMING OUT OF GENERATOR EXHAUST VENT, SHUT THE ENG DOWN USING THE ENG FIRE SWITCH, ABOUT 20 SECONDS AFTER THROTTLE TO CUTOFF. TROUBLESHOT TO STARTER GEN. REMOVED AND REPLACED NR 1 ENG STARTER GEN. OPS CHECK GOOD ALL WORK DONE IAW MM 80-11-01.

Part: BRAKE SYS — WEAK (MLG)

CAPTAIN AND COPILOT RIGHT BRAKE PEDALS ARE LESS EFFECTIVE THEN THE LEFT PEDAL, MORE TRAVEL IS NEEDED TO PRODUCE BRAKE PRESSURE. ACCOMPLISHED TASK CARD TC-560-32-080602. BLED BRAKES IAW ENGINEERING MEMO M344-08-10. TAXI CHECK GOOD.

Part: BRAKE SYS — MALFUNCTIONED · airframe 9,705 hrs · 7,979 cycles

ON TAXI OUT BOTH PILOT AND CO-PILOT BRAKES WERE VERY HARD DURING APPLICATION, WHEN BRAKES WERE APPLIED (CO-PILOT OR PILOT), AIRCRAFT WOULD NOT SLOW UNTIL A GREAT DEAL OF PRESSURE WAS APPLIED. SUSPECTED AIR IN SYSTEM, BLED LEFT & RIGHT BRAKES SEVERAL TIMES & PERFORMED SEVERAL OPS CHECKSOF LEFT & RIGHT SIDE PEDALS WITH NO DEFECTS IAW BRAKE BLEEDING PROCEDURE REVISED MEMO M344-08-106 MM 32-42-00.

Part: FLOW DIVIDER — OUT OF ADJUST (LT ENGINE) · airframe 9,646 hrs · 7,925 cycles

DURING SPEED BRAKE TEST, LT ENGINE SHUTDOWN AND RT ENGINE SHUTDOWN. ADJUSTED TENSION ON BALL PLUNGER ON THE FUEL FLOW DIVIDER, PERFORMED OPS CHECK WITH NO DEFECTS NOTED REF ENGINE MM 71-01-03

Part: SQUAT SWITCH — READS HIGH (LT MLG) · airframe 9,333 hrs · 7,682 cycles

LOST CABIN PRESSURIZATION AT FL290. CABIN PRESSURE ROSE TO 13500 PA AND STABILIZED. ON DESCENT, CABIIN PRESSURE DESCENDED WITH THE AIRCRAFT ALTITUDE. FOUND LT SQUAT SWITCH TO HAVE HIGH RESISTANCE AND CHANGING WITH PRESSURE ON ARM. REPLACED SWITCH WITH NEW IAW 560 MM 32-61-00. OPS CKED GOOD.

Part: BRAKE — FAILED (MLG) · airframe 7,985 hrs · 6,528 cycles

ON TAXI OUT DURING BRAKE CHECK CAPTAINS LEFT BRAKE WENT ALL THE WAY TO THE FLOOR. UPON ACTIVATION OF THE CO-PILOTS LEFT BRAKE, BOTH BECAME SPONGY. RESET BRAKE SHUTTLE VALVES, BLED BRAKE SYSTEM. PERFORMED SEVERAL BRAKE CHECKS STILL AND WHILE TAXIING WITH POWER BRAKE SELECTED ON AND OFF. NEVER GOT BRAKES TO FAIL. SOLID BRAKE PEDALS AT ALL TIMES IAW MODEL 560 MM 32-42-00.

Part: ENGINE — MALFUNCTIONED (RIGHT) · airframe 7,788 hrs · 6,362 cycles

ABORTED TAKEOFF, RIGHT ENGINE WOULD NOT MAKE TAKEOFF POWER (97.2) ONLY ACHIEVED 95.3 PERCENT. RAN RIGHT ENGINE TO TAKEOFF POWER [97.2], ALL PARAMETERS WERE WITHIN ACCEPTABLE LIMITS IAW CE 560 MM 71-01-02.

Part: RELAY — FAILED (ANTI SKID SYS) · airframe 6,886 hrs · 5,614 cycles

400 FT ABOVE TOUCHDOWN THE POWER BRAKE LOW PRESSURE AND ANTI-SKID INOP ANNUNCIATOR LIGHTS INOP LIGHTS ILLUMINATED AND THE ANTI-SKID CB POPPED, AND BRAKES BECME INEFFECTIVE - TESTED ANTI-SKID SYSTEM, BREAKER WOULD NOT TRIP, METERED ALL ANTI-SKID WIRES, FOUND NO SHORTS. INSPECTED ALL ANTI-SKID COMPONENTS, NO DEFECT NOTED, REPLACED SKID MOTOR CONTROL RELAY, SKID CONTROL RELAY, AND SKID CONTROL BREAKER IAW CESSNA 560 MM. CHAPTER 32-40-01. BLED BRAKE SYSTEM IAW CESSNA 560 MM CHAPTER 32-42-00, SERVICED EMERGENCY BRAKE BOTTLE IAW CESSNA 560 MM CHAPTER 12-13-01 BRAKE SYSTEM OPS CHECK GOOD.

Part: CONNECTOR — CONTAMINATED (ANTI SKID SYS) · airframe 6,882 hrs · 5,612 cycles

400 FEET ABOVE TOUCHDOWN THE POWER BRAKE LOW PRESSURE AND ANTI-SKID INOP ANNUNCIATOR LIGHTS INOP LIGHTS ILLUMINATED AND THE ANTI-SKID CB POPPED. - BLED AIRCRAFT BRAKE SYSTEM IAW CESSNA 560 MM CHAPTER 32-42-00. SERVICED EMERGENCY BRAKE BOTTLE IAW CESSNA 560 MM CHAPTER 12-13-01, FOUND ANTI-SKID CONTROL BOX CONNECTOR TO HAVE HYDRAULIC FLUID INSIDE CONTROL BOX AND NOTICED A BURN ODOR. CHECKED ALL HYDRAULIC LINES FOR LEAKS, REMOVED AND REPLACED ANTI-SKID CONTROL BOX IAW CESSNA 560 MM CHAPTER 32-42-00.

Part: CIRCUIT BREAKER — TRIPPED (ANTI SKID SYS) · airframe 6,881 hrs · 5,611 cycles

APPROX 100 FT ABOVE TOUCHDOWN THE "POWER BRAKE LOW PRESS." AND "ANTISKID INOP." ANNUNCIATOR LIGHTS ILLUMINATED AND THE ANTI SKID CIRCUIT BREAKER POPPED. LANDING WAS UNEVENTFUL, USED BACKUP PNEUMATIC SYSTEM TO STOP AIRCRAFT. - RE-SET CIRCUIT BREAKER WITH NO SUBSEQUENT POPPING, INSPECTED LT CIRCUIT BREAKER PANEL WITH NO FAULTS NOTED. BLED BRAKE SYSTEM TWICE TO REMOVE ALL AIR IAW CESSNA 560 MM CHAPTER 32-42-00. OPS CHECK & LEAK CHECK GOOD, SERVICED PNEUMATIC GEAR BOTTLE IAW CESSNA 560 MM CHAPTER 12-13-01.

Part: WARNING LIGHT — ILLUMINATED (ANTI SKID SYS) · airframe 6,875 hrs · 5,605 cycles

ON APPROACH POWER BRAKE LOW PRESS AND ANTI-SKID INOP, ANNUNCIATORS ILLUMINATED. EMERGENCY CHECKLIST PROCEDURE WAS COMPLIED WITH AND ANNUNCIATOR REMAINED ILLUMINATED. LANDING WAS MADE AND BRAKING ACCOMPLISHED USING BACK UP PNEUMATIC SYSTEM. ITEM IS UNDER INVESTIGATION.

Part: WIRE — BROKEN (FUSELAGE) · airframe 6,266 hrs · 5,096 cycles

LEFT THRUST REVERSER UNLOCK LIGHT CAME ON DURING TAKEOFF ROLL. ABORTED TAKEOFF. BLED BRAKE SYSTEM, TROUBLESHOT TO BROKEN WIRES ON THE ANTI-SKID TRANSDUCER. REPAIRED WIRING, PERFORMED OPERATIONAL CHECK AND TAXI CHECK OF THE BRAKE SYSTEM, CHECKED GOOD. ALL WORK DONE IAW CESSNA CE 560 MM CHAPTER 32-42-00 AND CHAPTER 32-40-01 OF THE CE560 WIRING DIAGRAM MM.