N614QS

Part: PCB — DEFECTIVE (ZONE 800) · airframe 9,464 hrs · 7,357 cycles

ANNUNCIATOR WARNING SYSTEM: CABIN DOOR WARNING LIGHT ILLUMINATED AS AIRCRAFT WAS IN A CLIMB AND PASSING THROUGH 33,000'. REPEAT GRIPE. REMOVED CABIN DOOR PCB NZ007 P/N:6618707-26 S/N:0282 INSTALLED CUSTOMER SUPPLIED NEW CABIN DOOR PCB NZ007 P/N:6618707-26 S/N:0653 WORK DONE IN REF TO CE-560XLS AMM 24-51-02 AND 52-70-00. OPS CHECK GOOD.

Part: NONE — NONE · airframe 13,967 hrs · 10,822 cycles

WHILE IN CRUISE AT 40,000 FEET, WE GOT THE "CABIN DOOR" ANNUNCIATOR. WE FOLLOWED THE QRH AND DIVERTED. UPON ARRIVAL T E DOOR PINS WERE INTACT AND LOCKED. // SIGNOFF// ATTEMPTED TO REPRODUCE PILOT WRITE UP. PERFORMED DOOR WARNING SYSTEM - OPERATIONAL CHECK IAW CE560XL AMM 52-70-00. MADE SEVERAL ATTEMPTS TO REPRODUCE PILOT WRITE UP. UNABLE TO REPRODUCE. CABIN DOOR WARNING IN GOOD OPERATIONAL CONDITION. CONTACTED NETSJETS MCC AND THEY ELECTED TO CLEAR MEL. MAINTENANCE ACTIONS CLEAR MEL

Part: NONE — NONE · airframe 10,790 hrs · 13,928 cycles

ENGINE COMPRESSOR STALL: AT CRUISE ALTITUDE 410 HEARD A LOUD BANG AND FELT A THUMP IN OUR FEET. N1 DROPPED FROM 91.0 TO 85 THEN RETURNED TO 91.0. REST OF FLIGHT WAS NORMAL. 2ND WRITEUP. ENGINE SYNC WAS OFF. // SIGNOFF// BEGAN TO TROIBLESHOOTING THE R/H ENGINE STALLING. COMPLIED WITH VISUAL INSPECTION OF THE ENTIRE ENGINE. INSPECTED THE FIRST STAGE BLADES AND INLET SECTION NO DEFECT NOTED, INSPECTED THE EXHAUST SYSTEM STATOR BLADES FOR ANY ISSUES NO VISUAL DEFECT NOTED, CHECK THE OIL LEVEL AND FOUND IN THE CORRECT LEVEL. OPEN END THE R/H ENGINE COWLING INSPECTED THE THROTLE CABLE IN THE FCU FOR A FREE MOVEMENT CLEARANCE CHECK NO DEFECT NOTED. CHECK FOR OIL OR FUEL LEAKS NO DEFECT NOTED • CLOSED THE R/H ENGINE COWLING AND STARTED THE R/H AND L/H ENGINE ALL SECUENCE FOR THE STARTING PROCESS TO THE IDLE PERFORMANCE AND THE PARAMETER ARE THE SAME AS THE L/H ENGINE AND COULD NOT BE DUPLICATE THE DISCREPANCY NO CAS MESSAGE OR DEFECT NOTED. DURING THIS TEST. NEED TO COMPLY HIGH ENGINE RUN AND POWER OHHE DAY TO CHECK THE HIGH PERFORMNCE RUN UP • ACCOMPLISHED THE ENGINE DOWNLOAD AND SENT TO PRATT &. WHITNEY FOR REVIEW , AIRCRAFT IS PLACED IN STAND BY AND WAJTNG FOR PRATT AND WHITNEY TECHNICAL SUPPORT FOR THE RECOMENDATIONS. WORK DONE REF CE· 560XLS MM CE-05·50·00 AND 76·11·00 AFTER REVIEWING THE DATA SENT EARLIER PWC REACHED OUT AND ADVISED US THE FILES SENT OVER WERE BLANK. DOWNLOADED THE RH ENGINE DCU AGAIN AND SENT TO PWC FOR REVIEW. ONCE AGAIN THEY ADVISED THE FILES SENT OVER WERE EMPTY. PER ROB AT PWC THE RH EN(;INE DCU WAS REINITIALIZED, AFTER RE-INITIAUZION ANOTHER DOWNLOAD WAS COMPLETED AND THE DATA SENT, AFTER REVIEW, ROB AT PWC ADVISED THE RE-INITIALIZATION FIX THE MISSING DATA ISSUE. HE ALSO NOTED THERE IS A FI-18 FAULT CODE ASSOCIATED WITH THE DIP IN N1 DISCRIBED IN THE DISCREPANCY, THE RH ENGINE TORQUE (TM) WAS CHANGED RECENTLY, CLOSE INSPECTION OF THE NEWLY INSTALLED MOTOR REVEALED IT IS PRE (SB) AND NOT POST (SB) AS SHOULD BE INSTALLED IN THE AC. OUR NEXT STEP ACCORDING TO STEVEN STRINE@ PWC IS: PLEASE ACCOMPLISH THE WIRING CHECKS.PER THE F1•18 AND ALSO THE BOY TQ MOTOR CHECKS PER 75-30, LET US KNOW WHAT YOU FIND AS THIS WILL HELP DETERMINE IF THE TQ MOTOR IS BAD OR WHERE WE NEED TO GD NEXT, FAULT CODE F'I-18 FOUND IN PWC545B EMM TASK: 72·00•00 • TORQUE MOTOR CHECKS CAN BE FOUND IN75•30-00 AS WE DISCUSSED ACCOMPLISHED THE WIRING CHECKS PER THE FI-18 AND ALSO THE BOV TQ MOTOR CHECKS PER 75-30. COMPLIED INSPECTION CHECK ON THE TORQUE MOTOR VERIFIED THE RESISTANCE ON THE TORUE MOTOR FOUND 077,6 OHMS AND IS IN LIMITS SHOULD BE 37 AND 200 OHMS. TORQUE MOTOR RESISTANCE CHECK GOOD. COMPLIED WIIRNG ON PIO WITH PL EEC INSPECTED FOR CONTINUITY THE PINS 5 WITH D NO DEFECT NOTED. INSPECTED THE PIN 1 WITH NO DEFECT NOTED. BOTH WIRES OHMED AND GROUND CHECK NO DEFECT NOTED. INSPECTED ALL THE PINS AND GROUND CONNECTORS FROM THE AIRFRAME CONNECTOR P7 WIRING CHECK ( NL) CHECK THE PIN 1 WITH D NO DEFECT NOTED, CHECK THE PIN 2 AND U NO DEFECT NOTED ,INSPECTED THE PIN 3 WITH 30 AIRFRAME CONNECTOR NO DEFECT NOTED • INSPECT THE WIRING INSULATION FOR CHAFFLNG OR ANY DAMAGE VISUAL INSPECTION CHECK GOOD , CLEANED CONNECTOR FOR P1, P7 ,PLO INSPECTED THE PINS AND CONNECTORS FOR A PROPER INSTALLATION ALL WIRING CHECK GOOD. IAW P&W 545B ENGINE GENERAL FAULT ISOLATION 72-00-00. REV 33 DATED. MOVED AC TO A SUITABLE ENGINE RUN AREA AND OPERATED THE ENGINES AND LEAK CHECKED THE LINES CALLED OUT ABOVE. NO LEAKES NOTED REMOVED EEC PN 1004855-2-002 SN 07010853 AND INSTALLED EEC FROM SISTER ENGINE PN 1004855-1-002 SN 06054554 FOR TROUBLESHOOTING PURPOSES. ASSISTED CUSTOMER WITH SATISFACTORY LEAK CHECKS AND GROUND RUNS IAW EMM 71-00-00 TABE 501 , ENGINE AUTHORIZED FOR RETURN TO SERVICE.NO APPLICABLE AD'S OR SB'S AT THIS TIME. ALL WORK PERFORMED IN ACCORDANCE WITH PW545B MAINTENANCE MANUAL, PART NUMBER 30J2242, REVISION# 33, DATED 9/13/2021 AND/OR APPLICABLE SERVICE BULLETINS. REMOVED BOV ASSY FOLLOWING REPORTED ENGINE STALL AT ALTITUDE. PERFORMED VISUAL INSPECTION OF BOVASSY AND LVDT, FOUND TO BE SERVICEABLE AT THIS TIME. REINSTALLED WITH NEW PACKING. REMOVED BOV TORQUE MOTOR PN 30J3490-01 SN TRAXY000299 AND REPLACED WITH NEW PN 30J4132- 01 SN TRAXY000008 PER CUSTOMER REQUEST. REMOVED SERVICEABLE BOV ORIFICE FROM REMOVED TORQUE MOTOR AND INSTALLED ON NEW TORQUE MOTOR. REMOVED EEC PN 1004855-1-002 SN 06054554 AND INSTALLED EEC FROM SISTER ENGINE PN 1004855-2-002 SN 07010853 FOR TROUBLESHOOTING PURPOSES, ASSISTED CUSTOMER WITH SATISFACTORY LEAK CHECKS AND GROUND RUNS IAW EMM 71-00-00 TABLE 501, ENGINE AUTHORIZED FOR RETURN TO SERVICE

Part: NOT REPORTED — NOT REPORTED · airframe 13,860 hrs · 10,742 cycles

LEFT FORWARD EMERGENCY LIGHT STRIP ON THE CABIN FLOOR, IS INOP///SIGN-OFF///RESEATED CONNECTORS AT FWD LIGHT ASSY. SYS CK GOOD.. ALL WORK PER CESSNA MODEL 560XL MM 33-20-00.

Part: BATTERY — DEFECTIVE (EMERGENCY LIGHTS) · airframe 13,490 hrs · 10,462 cycles

EMERGENCY LIGHTING: AFT EMERGENCY DIVIDER LIGHTS VERY DIM DURING PRE-FLIGHT CHECKS. ALL THREE EXTERIOR OVER WING EMERGENCY LIGHTS NOT ILLUMINATING. AFT EMERGENCY BATTERY PACK ISSUE SUSPECTED, NEED INSPECTION. ALL THE EMERGENCY UGHTS ARE WORKING WHILE CHARGING THE BATTERY PACKS. BUT THE AFT BATTERY PACK UGHTS DIM QUICKLY ON THEIR OWN, NEEDS THE BATTERY PACK MCC HAS ON ORDER. P.0.0. SL 09 03. ' REMOVED AND REPLACED AFT EMERGENCY UGHT BATTERY PACK WITH A SERVICABLE BATTERY PACK IAW CE-560XLS AMM 33-50·01. OPERATIONAL CHECKS SATISFACTORY. PN OFF 9913·1' SN OFF 1548 PN ON 9913·1 SN ON 670.

Part: TRANSDUCER — DEFECTIVE (ANTI-SKID SYS) · airframe 11,709 hrs · 9,116 cycles

ANTI SKID - DURING TAKEOFF ROLL & PRIOR TO V1, THE ANTI-SKID LIGHT ILLUMINATED. THE F/O CALLED ABORT, APPLIED BRAKING AND T/R'S. APPROXIMATELY, 1500 FEET PRIOR TO THE AIRCRAFT EXITING THE RUNWAY, I STARTED TO LOSE DIRECTIONAL CONTROL. "CORRECTIVE ACTION" REMOVED ANTI-SKID CONTROL BOS P/N 9912489-9 S/N 578 AND INSTALLED CONTROL BOX P/N 9912489 S/N 750. FOUND LT MLG WHEEL SPEED TRANSDUCER WITH ONE MOUNT SCREW TOO LONG CAUSING TRANSDUCER DIFFICULT TO SPIN. REMOVED AND REPLACED LT MLG WHEEL SPEED TRANSDUCER P?N 9912305-2 S/N 7202 AND INSTALLED TRANSDUCER P/N 9912305-2 S/N 2893.

Part: SKIN — CRACKED (RUDDER TAB) · airframe 11,617 hrs · 9,035 cycles

RUDDER TRIM TAB WELL APPEARS TO HAVE A RIVET PULLING OUT. PERFORMED PRELIMINARY INSPECTION OF DAMAGE AND NOTED CRACKED SKIN AT AFT SPAR COMMON TO PULLED FASTENER. PERFORMED REPAIR TO TRAILING EDGE OF RUDDER IN TRIM TAB WELL PER ERO-958235 REV IR DATED 5/20/2019. SEE ATTACHED FAA FORM 8110-3 DATED 05/21/2019 (DERT-750225-CE) FOR REPAIR AUTHORIZATION.

Part: APU — DEFECTIVE (APU BAY) · airframe 8,267 hrs · 6,447 cycles

GRAY SMOKE FILLED COCKPIT AND CABIN ON GROUND. APU WAS RUNNING WITH ACM. IMMEDIATELY SHUT DOWN APU AND ALL ELECTRICAL POWER. ENGINES WERE NOT RUNNING. SMOKE ODOR UNIDENTIFIED. COMPLIED WITH INSPECTION OF THE APU CONTAINMENT BOX AND CLEANED BLEED VALVE DUCTS, CLEANED WATER SEPARATOR AND COMPLIED WITH ENGINE RUN UPS. RAN APU. WHEN B/A VALVE OPENED COCKPIT FILLED WITH GRAY SMOKE. RAN APU FOR 1.5 HRS. NOTED APU OVER 1 QUART LOW. NOTED NO LEAKS IN APU CONTAINMENT BOX OR IN DRAINS. INSPECTED APU AND FOUND OIL RESIDUE IN INTAKE, REMOVED DEFECTIVE APU AND REPLACED WITH A REPAIRED APU, IAW CE-560XL MM 49-00-00. COMPLIED WITH APU RUN UP. OP CHECK IS GOOD AT THIS TIME. NO DEFECTS NOTED.

Part: UNKNOWN — ODOR (CABIN) · airframe 7,372 hrs · 5,756 cycles

DURING TAXI OUT, SMELLED A STRANGE OIL TYPE ODOR AND NOTICED THE APU HAD SHUTDOWN. STOPPED AND INSPECTED EXTERIOR AND FOUND NOTHING OUT OF THE ORDINARY. ACCOMPLISHED A SUCCESSFUL APU TEST THEN STARTED IT AGAIN. SUPPLY AIR WAS AT AMBIENT TEMP. SHUTDOWN THE APU. NO ODOR WAS NOTED WITH ENGINES RUNNING.

Part: SPRING — BROKEN (METERING VALVE) · airframe 7,268 hrs · 5,670 cycles

WHEN NORMAL BRAKES ARE APPLIED AFTER LANDING, LEFT BRAKE PEDAL HAS VERY LITTLE RESISTANCE. DEPRESSES MUCH FARTHER THAN RIGHT PEDAL, CAUSING ACFT TO TURN LEFT. THIS OCCURS WITH BOTH CAPT AND F/O BRAKES. BLED BRAKES TWO TIMES EACH SIDE IAW MM 32-44-00. LT BRAKE PEDAL STILL HAS LESS RESISTANCE THAN RT PEDAL. INSPECTED BRAKE METERING VALVE AND FOUND LT SPRING BROKEN AND RT SPRING CORRODED. REPLACED BRAKE METERING VALVE SPRINGS WITH NEW AND REPLACED ATTACH HARDWARE WITH NEW. TAXIED ACFT AND BRAKES OPS CHECKED GOOD IAW MM 32-44-20.

Part: STRUT — DISCHARGED (NLG) · airframe 5,457 hrs · 4,270 cycles

RAISED LANDING GEAR AFTER TAKEOFF AND RED UNLOCK LIGHT STAYED ON. ALL GREEN INDICATORS WENT OUT. IN ADDITION THE HYD PRESSURE STAYED ON AND STAB MISCOMPARE LIGHT CAME ON. PERFORMED COMPLETE NOSE GEAR STRUT SERVICING IAW MM 12-14-00. GEAR AND STAB OPS CHECKED GOOD.

Part: DOWNLOCK SWITCH — MALFUNCTIONED (MLG) · airframe 2,411 hrs · 1,876 cycles

RT GEAR INDICATOR LIGHT SHOWED RT GEAR NOT DOWN AND LOCKED. PEFORMED GEAR SWING MANY TIMES WITH NO FAULTS. APPLIED FREEZE-IT SPRAY TO RT GEAR DOWNLOCK SWITCH GIVING US A FAULTY LIGHT AT GEAR INDICATION. REMOVED RT MAIN ACTUATOR AND INSTALLED REPAIRED ACTUATOR IAW MM 32-30-04 AND CESSNA ENGINEER LETTER DATED 1/10/08. FUNCTIONAL CHECK AND LEAK CHECKS GOOD. SERVICED AND SAFETIED GEAR PNEUMATIC BOTTLE.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 736 hrs · 548 cycles

ANTI-SKID LIGHT ILLUMINATED ON SHORT FINAL. LOW BRAKE PRESSURE LIGHT FOLLOWED DURING TAXI. EMERGENCY BRAKE SYSTEM WAS UTILIZED. PWR BRK CIRCUIT BREAKER HAS POPED OUT. INSPECTED PWR BRAKE ANTI SKID SYSTEM. FOUND GEAR BRAKE PNEUMATIC BOTTLE PSI TO BE 1950 PSI AT 70 F (PROPER LEVEL) PNEUMATIC BOTTLE VALVE WAS FOUND ENCLOSED POSITION AND BREAK AWAY SAFETY WIRE WAS NOT BROKEN. BOTTLE WAS NEVER ACTUATED. OPS CHECKED PWR BRAKE SYSTEM, MOTOR AND PRESS SWITCHES. SYSTEM CHECKS GOOD. BRAKE RES AND PRECHARGE FOUND TO BE AT PROPER LEVELS. TAXI CHECKED ACFT WITH LIGHT TO HEAVY BRAKING. NO FAULTS FOUND, BRAKE SYSTEM, OPS NORMAL IAW MM 32-42-00.