N530QS

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 6,094 hrs · 4,083 cycles

ENG CNTRL FAULT R AMBER CAS: ENG CTRL FAULT R AMBER CAS MESSAGE DISPLAYED AFTER TAKEOFF. FOLLOWED THE CHECKLIST AND MESSAGE REMAINED. LANDED AS SOON AS PRACTICAL. ACCESED AIRCRAFT AND PERFORMED ENG RUNS. CYCLED T/R'S MULTIPLE TIMES IAW CE680A MM 78-30-00. SHUT DOWN ENGINES. NO CAS MESSAGES NOT FAULTS RECEIVED. ACCESSED THE CMC FOR AND ALERT ID# THE CREW RECEIVED WAS 1678. PERFORMED ARES DOWNLOAD AS PER MCC REQUEST AND SENT OVER. PERFORMED T /R EMER STOW PROCEDURES AS PER MCC IAW CE680A MM 78-30-00. ALL CHECKS SATISFACTORY. MCC OK TO SIGN OFF. OK TO CONTINUE.

Part: HARNESS — BROKEN (MAIN DOOR) · airframe 5,465 hrs · 3,676 cycles

MAIN DOOR: MAIN DOOR WILL NOT LOCK. DOOR WILL CYCLE INTO CLOSED POSITION BUT SOLIENOID WILL NOT CYCLE TO LOCK DOOR. REMOVED CHAFFED DOOR THRESHOLD HARNESS AND INST.AILED NEW HARNESS, WNPLETED OPS CHECKS WITH NO DEFECTS NOTED. ALL WORK AANMPLISHE IAW CE680A AMM 52-10-50 AND SB680A-52-05

Part: DOOR — UNKNOWN (MAIN) · airframe 5,465 hrs · 3,676 cycles

MAIN DOOR: MAIN DOOR WILL NOT LOCK. DOOR WILL CYCLE INTO CLOSED POSITION BUT SOLIENOID WILL NOT CYCLE TO LOCK DOOR.

Part: LUG — DAMAGED (ZONE 800) · airframe 5,140 hrs · 3,455 cycles

MAIN CABIN DOOR FORWARD FRAME P/N 7411305-37 LUG DAMAGED.

Part: CHARGER — NONE · airframe 4,635 hrs · 3,121 cycles

EMERGENCY LIGHTS (FLOOR ILLUMINATION) UNDER SEATS 5 & 8 INOP WHEN CHECKING EMERGENCY LIGHTS. *** CORRECTIVE ACTION *** ALLOWED EMERGENCY BATTERY PACKS TO CHARGE AND ATTEMPTED OPS CHECK THE EMERGENCY LIGHTS AND AGAIN SEATS 5, 8, AND OVERWING EMERGENCY LIGHT WOULD NOT STAY ILLUMINATED FOR LONG. THESE EMERGENCY LIGHTS ARE POWERED BY EMERGENCY BATTERY PACK #3.REMOVED FAULTY EMERGENCY BATTERY PN:CBS28-1 SN:005306. INSTALLED REPAIRED EMERGENCY BATTERY PN:CBS28-1 SN:2163M. OPS CHECKED GOOD, ALL EMERGENCY LIGHTS ILLUMINATED. CHARGED BATTERY FOR AN HOUR.

Part: FRAME — CRACKED (NLG WW) · airframe 3,311 hrs · 2,261 cycles

SR-680A-ATA53-25890 MAJOR REPAIR, CRACK DAMAGE, NOSE LANDING GEAR WHEEL WELL, FRAME , WEB AND DOUBLERS FS 75.

Part: SUPPORT FRAME — CRACKED (ZONE 100) · airframe 3,311 hrs · 2,261 cycles

NOSE LANDING GEAR WHEEL WELL FRAME CRACKS.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 2,951 hrs · 2,002 cycles

REPAIR OF HORIZONTAL STABILIZER LEFT LOWER SKIN DAMAGE (CORROSION). TEXTRON AVIATION ENGINEERING REPAIR LETTER DQ25592M1 DATED APRIL 29, 2020.

Part: SOFTWARE — MALFUNCTIONED (CABIN PRESSURE) · airframe 2,662 hrs · 1,820 cycles

CABIN ALTITUDE RED CAS ILLUMINATED, ENROUTE AT FLIGHT LEVEL 410. THE PRESSURIZATION FAULT CAS MESSAGE CAME ON. CHECKLIST HAD US GO TO MANUAL THEN AUTO AGAIN. FAULT LIGHT WENT OUT THEN IMMEDIATELY CAME BACK ON. WENT BACK TO MANUAL AND CABIN WAS CLIMBING RAPIDLY FOLLOWED BY THE GEA FAULT 3 CAS MESSAGE AND ENG CNTRL FAULT R CAS MESSAGES. DECLARED AN EMERGENCY AND EXECUTED A RAPID DESCENT. DURING THE DESCENT THE CABIN ALT RED CAS MESSAGE CAME ON AND THE PASSENGER OXYGEN MASKS DEPLOYED AUTOMATICALLY. THE MANUAL PRESSURIZATION MODE MADE THE CABIN INITALLY RISE RAPIDLY WHEN FIRST SELECTED ON BUT WERE ABLE TO GET IN UNDER CONTROL DURING DESCENT. ALL CAS MESSAGES CAME ON ONE RIGHT AFTER THE OTHER. PRIOR TO LANDING AT APPROXIMATELY 500 FEET AGL THE MFD, GTC 2, 3, AND 4 SLOWLY DIMMED AND THEN WENT BACK TO FULL BRIGHTNESS FOLLOWED BY ALL THE CAS MESSAGES GOING AWAY. PERFORMED A SOFTWARE BASE LOAD IAW LMM 190-01595-00 IN ORDER TO MAKE THE AMBER STATUS DISSIPATE AND HAVE A CURRENT UPDATED BASE LOAD. COULD NOT DUPLICATE THE ISSUES WRITTEN UP BY THE CREW. TEAM STATEED THAT THE SUCCESSFUL BASE LOAD WILL CLEAR UP THE RANDOM FAULTS THROWN DURING FLIGHT. HAVE CLEARED THIS ITEM FOR RELEASE. FOUND THAT THE TASK IN THE AMM WAS INCORRECT.

Part: SKIN — CHAFED (FUSELAGE) · airframe 2,337 hrs · 1,591 cycles

WING ANTI-ICE CROSS FLOW VALVE IS CHAFFING ON FUSELAGE LOWER SKIN. BLENDED OUT DAMAGE TO PREPARE FOR NDT. NO CRACKS NOTED. COMPLETED STANDARD REPAIR SR-680A-ATA53-22175.

Part: CIRCUIT BOARD — MALFUNCTIONED (FIRE DETECTION) · airframe 2,266 hrs · 1,529 cycles

ENGINE FIRE R RED CAS INTERMITTENT - DESCENDING THROUGH 7000FT, RED ENGINE FIRE R CAS ILLUMINATED FOR ABOUT 1 SECOND WITH ASSOCIATED AUREL MESSAGE RECOMMEND SWAPPING THE NC208 AND NC108 PCB'S. GAINED ACCESS TO PCB'S AND, REMOVED THE LJH PCB P/N: 6918632-12, S/N: 0401 AND INSTALLED THE SERVICABLE R/H PCB P/N: 6918632-12, S/N: 0387 IN THE LJH ENCLOSURE. REMOVED THE R/H PCB P/N: 6918632-12, S/N: 0387 AND INSTALLED THE SERVICABLE L/H PCB P/N: 6918632-12, S/N: 0401 IN THE R/H ENCLOSURE. PERFORMED OPS CHECK OF SYSTEM, CLEANED AND INPSECTED CONNECTOR PLUG ON R/H ENGINE, RAN ENGINES AND NO DEFECTS NOTED. ALL WORK IAW MM 24-60-00 AND 71-00-00.

Part: SWITCH — INOPERATIVE (FUEL BYPASS) · airframe 507 hrs · 371 cycles

DURING CRUISE AT FL 400, RECEIVED AN AMBER CAS MESSAGE FOR FUEL FILTER BYPASS RT. COMPLIED WITH QRH AND DIVERTED. DID NOT EXPERIENCE ANY ENGINE SURGING OR OTHER ANOMALIES. REMOVED AND REPLACED FUEL IMPEDING BYPASS DIFFERENTIAL SWITCH IAW MM 73-10-03.

Part: LINE — BROKEN (NR 1 ENGINE)

PILOT'S DISCREPANCY WAS NR 1 ENIGNE IS TEMP LIMITED ABOVE CRUISE DETENT. REMOVED THE OUTER AND INNER BYPASS ACCESS TO CHECK BLEED VALVES. UPON INVESTIGATION, FOUND THE BLEED AIR (P3 LINE) BROKEN AT B-NUT, P/N 3081695. IT APPEARED THE FIT OF THE LINE HAD CAUSED FAILURE BECAUSE THE 2 ENDS AT BREAK DID NOT LINE UP. REPLACED THE LINE WITH NEW. FIT WAS GOOD. RE-ASSEMBLED ENGINE. GROUND RUN AND FLIGHT CHECK WAS GOOD.

Part: P3 LINE — BROKE (NR 1 ENGINE)

PILOTS DISCREPANCY WAS NR 1 ENGINE TEMPORARILY LIMITED ABOVE CRUISE DETENT. REMOVED THE OUTBOARD INNER BYPASS ACCESS TO CHECK BLEED VALVES. UPON INVESTIGATION, FOUND THE BLEED AIR (P3 LINE) BROKEN AT B-NUT, P/N 3081695. IT APPEARED THE FIT OF THE LINE HAD CAUSED FAILURE BECAUSE THE 2 ENDS AT BREAK DID NOT LINE UP. REPLACED THE LINE WITH NEW. FIT WAS GOOD. RE-ASSEMBLED ENGINE. GROUND RUN AND FLIGHT CHECK WAS GOOD.