N512QS

Part: WIRE — PULLED (ZONE 200) · airframe 8,828 hrs · 5,985 cycles

LAV EMERGENCY TOE KICK LIGHT DOES NOT ILLUMINATE WITH ANY POWER SOURCE. REMOVED LAV FASCIA & FOUND THE WIRES FOR THE TOE KICK LIGHT PULLED OUT OF THE CONNECTOR. LOOKED UP & PLACED NEW CONNECTOR & PINS ON ORDER. 8/30 JT-VJG. INSTALLED NEW PINS ONTO WIRE & INSTALLED PINS INTO CONNECTOR, RECONNECTED WIRING TO LIGHT, OPS CHECKS GOOD IAW MM 33-50-00

Part: WARNING MESSAGE — FALSE INDICATION (ZONE 800) · airframe 8,633 hrs · 5,834 cycles

RECIVED CHECK DOORS CAS. FOLLOW CHECK DOORS QRH AND CYCLED ALL DOORS ASSOCIATED ALSO COMPLETED POWER UP ANOMALY CHECKLIST. CAS REMAINS WITH THE MAIN CABIN DOOR CLOSED. DOOR OPEN LIGHT ALSO REMAINS ON.(HANDLE STIFF AND NOT STOWING) POWERED UP ACFT. CONFIRMED ALL DOORS IN CLOSED CONFIGURATION, INTERIGATED CMC. NO CORELATING DATA NOTED. COMPLIED WITH ARES DOWNLOAD IAW MM 45-00-00 AND SENT TO TEAM 680A. CONTINUED TROUBLESHOOTING, PERFORMED MAIN ENTRANCE DOOR RESET PROCEDURE IAW AFM. AT THIS TIME, CLOSED THE MED. NO CHECK DOORS OR DOOR OPEN CAS MESSAGE NOTED. PERFORMED CABIN DOOR OPS CHECK IAW MM 52·10·00. FOLLWED UP WITH EMAIL TO TEAM 680A & MCC, NO RECENT HISTORY OF DISCREPANCY NOTED. NO FURTHER ACTION REQUIRED.

Part: CLOSEOUT PANEL — CORRODED (ZONE 500) · airframe 8,543 hrs · 5,772 cycles

CORROSION UNDER LH AND RH AFT WING TO FUSELAGE FAIRING SUPPORT STRUCTURE

Part: ANTI-ICE SYSTEM — FAULTED (ZONE 400) · airframe 8,403 hrs · 5,685 cycles

DURING CLIMB AROUND 14000' WE OBSERVED A/I ENGINE HOT R CAS MSG. WE RAN THE QRH PROCEDURE AND DECREASED RIGHT ENGINE POWER. THE MSG EXTINGUISHED. BUT THEN REOCCURED WHEN POWER WAS INCREASED. ENG BLD AIR KNOB WAS SECLECTED TO LP AND DIVERTED WHILE REMAINING CLEAR OF ICING CONDITIONS. CORRECTIVE ACTION: ACCESSED TO RAMP. PERFORMED ARES DOWNLOAD AND SEND IT TO TEXTRON TO REVIEW. RAN BOTH ENGINES AND CHECKED ENG A/I SYSTEM OPS CHECKS. IT APPEARS TO BE WORKING NORMAL ON GROUND. CHECKED LIVE DATA VIEW AND TEMPERATURE WAS INDICATIING NORMAL REPORTED TO MCC. TEXTRON INFORMED THE ARES DATA REVIEW. "ARES DATA LOOKS LIKE THE VALVE IS SLOW TO CLOSE". CHECKED WIRING FOR R/H AND FOUND SHIELD GROUND SPLICE WIRE PULLED FROM CONTACT. RE-CRIMPED WIRE TO CONTACT REF TO CE680 WDM CHAP30-00-02. CHECEKD POWER AND GROUND AT CONNECTOR PE011 GOOD. REPORTED TO MCC AND MCC ADVISED TO SWAP THE VALVE SIDE OT SIDE. GAINED ACCESS TO ENGINE INLET ANTI-ICE VALVES. SWAPPED VALVES BETWEEN VD003-LEFT AND VE003-RIGHT. PERFORMED LEAK AND OPS CHECKS GOOD ON GROUND. CLOSED ACCESS. WORK DONE JAW CE680A AMM CHAP 30-20-05. PARTS INSTALLED LJH: PN: 9914521-6 SN: 1501 R/H: PN: 9914521-6 SN: 1499 TORQUE WRENCH: TL-104390 CAL DUE SEP. 16 2025.

Part: FUSE — BLOWN (ZONE 200) · airframe 8,025 hrs · 5,450 cycles

DURING THE FIRST STEP OF THE POWER ON CHECKLIST, EMERGENCY LIGHTS DO NOT ILLUMINATE WITH THE SWITCH PLACED IN "ARM" (NO DC POWER ON). LIGHTS DO WORK IN THE "ON" POSITION. WE PERFORMED THE "EMERGENCY LIGHTS FAIL PREFLIGHT TEST" CHECKLIST VIA MAINTANENCE'S INSTRUCTIONS AND RECHECKED THE LIGHTS TWICE AFTER TWO 30 MINUTE CHARGING PERIODS FOR A TOTAL OF 60 MINUTES. AFTER BOTH CHARGING PERIODS THE LIGHTS STILL FAILED TO ILLUMINATE IN THE "ARM" POSITION. CORRECTIVE ACTION: REPLACED FUSE. OPS CHECK GOOD. IAW CE·680A AMM 33-50-00

Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 7,998 hrs · 5,430 cycles

EMER LIGHTS STILL ILLUMINATED IN ARM WTIH MAIN DC APPLIED. CYCLED TO COLD/ DARK AND RESET BUTTON, CONDITION STILL REMAINED. CORRECTIVE ACTION; CONFIRMED DISCREPANCY. ACTUATED ALL G SWITCHES, NO CHANGE TO CONDFFION. ELECTRICALLY CHECKED ALL G SWITCHES PER CE·680 MM 33·50·00, NO DEFECTS NOTED. NOTED THAT ALL EMER LIGHTS WERE ILLUMINATED IN ARM POSITION EXCEPT THE LIGHTS POWERED BY #1 BATTERY PACK. SWAPPED #1 AND #4 BATTERY PACKS, NO CHANGE TO CONDITION, INSTALLED #2 AND #3 BATTERY PACKS IN #1 POSITTON, ALL LIGHTS STILL ILLUMINATED IN ARM POSITION EXCEPT THOSE POWERED BY #1 BATTERY. WHEN PLACED IN ANY OTHER LOCATION THE ORIGINAL #1 BATTERY POWERED WHATEVER UGITTS ASSOCIATED WITH THAT POSITION. RETURNED ALL BATTERY PACKS TO THERE ORIGINAL POSITIONS. REFERENCE CE·680A MM 33-50·06. NOTIFIED MCC OF FINDINGS, THEY NOTED THAT KC007 RELAY COULD BE AT FAULT. TAPPED LIGHTLY ON RELAY AND ALL EMERGENCY LIGHTS STARTED FUNCTIONING AS THEY SHOULD. PERFORMED OPERATIONAL CHECK OF EMERGENCY LIGHTS PER CE·680A MM 33·50·00, NO DEFECTS NOTED. DUE TO FAULT BEING CUEAREO AND NO AVAILABILITY OF A REPLACEMENT RELAY MCC ELECTS TO RTS AT THIS TIME, NO OTHER DEFECTS NOTED.

Part: UNKNOWN — INOPERATIVE (UNKNOWN) · airframe 7,017 hrs · 4,741 cycles

GEA FAIL 3 AMBER CAS: GEA FAIL 3 CAS MESSAGE ILLUMINATED DESCENDING THROUGH FL 240. REMOVED GEA 3 PN 011-02635-00 SN 2BY005258 AND INSTALLED CUSTOMER SUPPLIED REPAIRED GEA7100 (UNIT 3) PN 011-02635-00 SN 2BY005444 AS REQUIRED. PERFORMED CONFIGURATION AS REQUIRED AND OPS CHECKS GOOD AT THIS TIME. ALL WORK PERFORMED IN REF TO AMM 31-40-15. ENGINE DISPATCH LIMIT / ENGINE MAINT LIMITED: ENGINE CONTROL FAULT R ILLUMINATED AMBER PASSING THROUGH FL 240. REMOVED GEA 3 PN 011-02635-00 SN 2BY005258 AND INSTALLED CUSTOMER SUPPLIED REPAIRED GEA7100 (UNIT 3) PN 011-02635-00 SN 2BY005444 AS REQUIRED. PERFORMED CONFIGURATION AS REQUIRED AND OPS CHECKS GOOD AT THIS TIME. ALL WORK PERFORMED IN REF TO AMM 31-40-15.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 6,785 hrs · 4,575 cycles

CABIN EMERG LIGHT: EMERGENCY LIGHT ABOVE SEAT 7 IS STUCK IN THE ON POSITION WHEN THE EMER LIGHT SWITCH IS IN ARM POSITION. LIGHT WILL NOT TURN OFF UNLESS EMER LIGHT SWITCH IS SET TO OFF POSITION. RESET THE #1 EMERGENCY LIGHT INERTIA SWITCH AS REQUIRED, OPERATIONAL CHECK IS GOOD, CHARGED EMERGENCY BATTERIES FOR 1 HOUR IAW AMM 33-50-00.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 6,382 hrs · 4,307 cycles

LAV EMERG LIGHT: THE EVACUATION PATH LIGHT UNDER THE LAV SEAT WAS FLICKERING ON AND OFF, AND THEN EXTINGUISHED. TRACED BACK TO A WIRE PUSHED PIN IN THE WIRING HARNESS CONNECTOR. RESEATED THE PIN INSIDE THE CONNECTOR & FOUND LIGHT ASSY TO WORK AS NORMAL. SECURED THE CONNECTION & RESTORED THE LAV TOILET. EMERGENCY FLOOR PATH LIGHTING CKS ARE GOOD & NO DEFECTS. WORK DONE WITH REF TO CE680A SPM 20-30-25 & AMM 33-50-00.

Part: ENGINE — CORRODED (ZONE 400) · airframe 5,513 hrs · 3,738 cycles

LH ENGINE AGB AFT COVER IS CORRODING.

Part: ENGINE — CORRODED (ZONE 400) · airframe 5,513 hrs · 3,738 cycles

RH ENGINE AGB AFT COVER IS CORRODING.

Part: SWITCH PANEL — DEFECTIVE (ZONE 800) · airframe 5,087 hrs · 3,471 cycles

LIFT BLACK BUTTON LOCATED IN THE CABIN WHICH FUNCTIONS TO CLOSE THE MAIN CABIN DOOR IS INTERMITTENT WHEN PRESSED TO LIFT THE DOOR. // SIGN OFF// GAINED ACCESS TO SWITCH PANEL REMOVED AND REPLACED SWITCH PANEL PN: SWP500-01 SN: 277000086 WLTH INSPECTED SWITCH ASSY SWP500-01 SN 277000225. RESTORED ALL ACCESS. OPS CHECK GOOD REF 680A AMM 52-15-00 AND AMM 52-15-05

Part: PCB — DAMAGED (ACM) · airframe 4,934 hrs · 3,374 cycles

ACM BLD LEAK AMBER CAS: AT FLIGHT LEVEL 220, THE ACM BLEED LEAK QUICKLY FOLLOWED BY THE EMER PRESS CAS MESSAGES ILLUMINATED. WE COMPLETED THE ACM BLEED LEAK AND EMER PRESS QRH CHECKLISTS. THE CABIN TEMP WENT TO 124 DEGREES AND THE COCKPIT TEMP WENT TO 93 DEGREES. THE APU WOULD NOT START IN THE AIR OR ON THE GROUND. WE COULD NOT CONTROL THE TEMP SUPPLY BY ANY MEANS. OUR PASSENGERS CONTINUALLY UPDATED US ON THE HOT CABIN TEMP AND SMELL. R & R APU CONTROL PCB WITH A NEW UNIT. PERFORMED OPS CHECKS OF SYSTEM NO DEFECTS NOTED. WORK DONE IAW CE-680AS AMM 24-60-35.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 4,737 hrs · 3,230 cycles

HORIZONTAL STABILIZER LOWER SKIN DAMAGE(CORROSION).

Part: DOUBLER — CRACKED (NLG WW) · airframe 3,958 hrs · 2,709 cycles

CRACK DAMAGE, NOSE LANDING GEAR WHEEL WELL. ACCOMPLISHED TEXTRON AVIATION FIELD REPAIR SR-680A-ATA53-25890 REV- DATED 6/1/2020: STANDARD REPAIR-CRACK DAMAGE, NOSE LANDING GEAR WHEEL WELL NWW, FRAME, WEB, AND DOUBLERS, FS 75.

Part: FILTER — DIRTY (CABIN AIR) · airframe 2,003 hrs · 1,421 cycles

AFTER TAKEOFF, SMOKE APPEARED IN CABIN (LIGHT HAZE) AND ACRID SMELL. SUPPLEMENTAL INFORMATION: REMOVED AND REPLACED CABIN HEPA FILTER IAW CE680A MM 21-70-10. REMOVED PN 9914836-1 SN 0102. INSTALLED PN 9914836-1 SN 0244

Part: SHROUD — DETACHED (RT AILERON) · airframe 88 hrs · 57 cycles

RIGHT WING AILERON TRAILING EDGE SHROUD FORWARD OF THE AILERON HAS BECOME DETACHED. THE SHROUD IS ATTACHED TO THE WING VIA 8 SCREWS. THE TRAILING EDGE WING STRUCTURE THAT THE SHROUD ATTACHED TO FAILED AT 3 SCREW ATTACH POINTS AT THE TOP AND 2 AT THE BOTTOM ARE BEGINNING TO FAIL AS WELL. REMOVED AND REPLACE TWO ANGLE ASSYS, CENTER SHROUD (CLOSE OUT PANEL), AND RT AILERON ASSEMBLY IAW DRAWING 6922690, SRM 51-40-05, AND MM 57-60-00. AILERON OPERATION AND TRAVEL CHECKS GOOD. AILERON INSTALLATION IAW MM 57-60-05.