N562QS

Part: SUPPORT — CRACKED (ZONE 100) · airframe 8,241 hrs · 5,479 cycles

LH FWD WHEEL WELL FAIRING SUPPORT FRAME P/N 6910269-49 CRACKED AT RIVET.... EDDY CURRENT NDT INSPECTION PERFORMED BY TOLEDO JET CENTER, CRS# 2TJR420B. CRACK TIP(S) IDENTIFIED ON ARTICLE, COMPLETED STEPS 1-18 OF RFTS-115292 REV. 0 (DRAFT). FABRICATED -001 DOUBLER FROM 0.050IN 2024-T3 PER AMS-QQ-A-20/5 SHEET STOCK. MATCH DRILLED REMAINING DOUBLER HOLES AND INSTALLED OEM RIVETS. REF. RFTS-115292 REV. 0.

Part: GSD — FAULTED (ZONE 200) · airframe 8,241 hrs · 5,479 cycles

GSD 3 FAIL AMBER CAS MESSAGE CAME ON IN FLIGHT, HAD FAILURE INDICATIONS FOR ASSOCIATED SYSTEMS. CORRECTIVE ACTION: REMOVED AND REPLACED GARMIN #3 GSD-41 (DCU) IN REF TO CESSNA 680A MM 31-40-10. COMPLIED WITH #3 GSD-41 OPERATIONAL CHECK (SOFTWARE AND CONFIGURATION LOADING) IN REF TO CESSNA 680A MM 31-40-00, STEP 10.A.(1). COMPLY WITH REMAINING #3 GSD OPERATIONAL CHECKS. / GSD3

Part: SWITCH — DEFECTIVE (MAIN DOOR) · airframe 7,161 hrs · 4,751 cycles

CABIN DOOR OPEN AMBER CAS: ENROUTE AT FL430 WE RECEIVED AMBER CHECK DOORS AND CABIN DOOR OPEN CAS MESSAGES SIMULTANEOUSLY. FOLLOWING THE CHECKLIST WE WERE DIRECTED TO RAISE THE CABIN ALTITUDE, DESCEND, AND LAND AS SOON AS PRACTICAL. WE ELECTED TO DIVERT TO CMH, IT WAS APPROXIMATELY 30 MINUTES AWAY. CORRECTIVE ACTION; POWERED UP AIRCRAFT WE HAD HARD FAULTS CABIN DOOR OPEN AMBER CAS AND CHECK DOORS WITH CABIN DOOR AND ALL OTHER DOORS CLOSED. WHEN WE BEGAN TROUBLESHOOTING DOOR REPORT AND FOUND A ¿PAWL DOOR SWITCH¿ DISCREPANCY, PLUS THE PAWL SOLENOID WAS NOT ENERGIZING. REMOVED AND CLEANED CONNECTOR ON ON PAWL PROX SWITCH AND VERIFIED PROX SWITCH OPERATION WITH TARGET AND INDICATOR LIGHTS. REMOVED AND INSPECTED NC105 PCB, NO DEFECTS NOTED. RE-INSTALLED NC105, REF CE 680A MM 24-60-40, AFTER RE-INSTALLING NC105 PAWL SOLENOID BEGAN WORKING AND ALL CAS MESSAGES EXTINGUISHED. DOOR INDICATIONS OPS CHECKS GOOD. REF CE 680 MM 52-70-00, 31-59-00. HARD FAULT NO LONGER PRESENT. AFTER REVIEWING ARES DATA FOUND INTERMITTENT INFLIGHT FAULT FROM UPPER FORWARD DOOR PROX SWITCH SC002. REMOVED AND REPLACE SC002, REF CE 680A MM 52-70-10. OPS CHECK GOOD.

Part: NONE — ERODED (ZONE 300) · airframe 4,186 hrs · 2,758 cycles

LH HORIZONTAL STAB CUFF PANEL LEADING EDGE IS ERODED INTO THE COMPOSITE. THE REPAIR WAS DEEMED MINOR IN SCOPE. REPAIRED PER TEXTRON AVIATION ENGINEERING MEMO DQ34098M1 DATED MAR 23, 2022.

Part: COWLING — ERODED (ZONE 400) · airframe 4,186 hrs · 2,758 cycles

LH ENGINE LOWER COWL HAS AN AREA DELAMINATED ALONG THE LEADING EDGE. THE REPAIR WAS DEEMED MINOR IN SCOPE. REPAIRED PER TEXTRON AVIATION ENGINEERING MEMO DQ34060M1 DATED MAR 21, 2022.

Part: WEB — CRACKED · airframe 4,186 hrs · 2,758 cycles

CRACKING IN NOSE WHEEL WELL STRUCTURE COMPONENTS: RH DOUBLER, P/N: 7413133-16, LH DOUBLER, P/N: 7413133-15, TOP WEB, P/N: 7413133-10, AND FRAME, P/N: 7413133-59

Part: AXLE — CHIPPED (RT MLG) · airframe 3,563 hrs · 2,351 cycles

RH MLG AXLE MISSING PLATING. ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER 31045M1 DATED AUGUST 12, 2021; 680A-0112 (N562QS) RIGHT MAIN LANDING GEAR AXLE PLATING DAMAGE (CHIPPED).

Part: BATTERY — FAULTED (MASTER) · airframe 3,508 hrs · 2,316 cycles

BATTERY OTEMP L RED CAS: BATTERY O TEMP CAS CAME ON AFTER TAKEOFF. RAN QRC MEMORY ITEM THEN QRH.RETURNED TO AIRPORT AND LANDED. ELECTRIC PAGE SHOW NO OVER VOLTS OR AMP PROBLEMS. SEVERAL SPURIUS CAS MASSAGES AT TAXI IN. COMPLETED RESISTANCE CHECKS ON BATTERIES AND WIRES AND FOUND RH BATTERY OVERHEAT SENSOR TO HAVE 4 PINS SHORTED TO GROUND. REMOVED FAULTY RH BATTERY AND INSTALLED A SERVICABLE IN THE RH POSITION.COMPLETED OPS CHECKS WITH NO DEFECTS NOTED, ALL WORK ACCOMPLISHED !AW CE680A AMM 24-30-05

Part: RESERVOIR — LOW (HYD SYSTEM) · airframe 3,351 hrs · 2,216 cycles

ENG CNTRL FAULT L AMBER CAS: AT FL350 THE AP AND AT KICKED OFF. FOLLOWED BY AN ENGINE CNTRL FAULT L-R CAS MESSAGE. WE PERFORMED THE QRH U1 AND DURING THE CHECKLIST THE CAS MESSAGE GIA FAIL 1 DISPLAYED. WE THEN RAN THE ORH Y1 WITH NO IMPROVEMENT. DECLARED AN EMERGENCY DUE TO NEGATIVE GEAR INDICATIONS ASSOCIATED WITH THE THE GIA FAIL. WE LOWERED THE GEAR DOWN THROUGH THE GEAR HANDLED AS WELL AS USED THE LANDING GEAR BLOW DOWN IN ACCORDANCE OF ORH Y1. FLEW BY TOWER FOR A VISUAL CONFORMATION AND THE PROCEED TO LAND. ON TOUCHDOWN DATABUS FAIL CAS MESSAGE DISPLAYED. WE PROCEED TO THE RAMP WITH NO OTHER ISSUES // SIGNOFF// REMOVED GARMIN GIA63W #1 PRT#0 11-01105-40 SRL#2DC0O 1287 AND INSTALLED REPAIRED GARMIN GIA63W #1 PRT#OL 1-011-5-40 SRL#2DC001342 AND LOADED APPROPRIATE SOFTWARE IAW MM 31-40-05. - GIA#L GROUND OPS CHECKS GOOD AT THIS TIME IAW MM 31-40-00 SECTION 6. PERFORMED APU, LT ENGINE, AND RT ENGINE START UP SHUTDOWN PROCEDURES WITH NO DEFECTS OR ENGINE CONTROL FAULTS NOTED. GEAR WAS BLOWN DOWN DUE TO GIA #1 FAILURE JACKED THE AIRCRAFT TO BLEED THE HYDRAULIC SYSTEM. RESET THE EMERGENCY GEAR BOTTLE ARM AND RESERVICED TO 2000 PSI IAW MM 12-10-45. THE LANDING GEAR CONTROL MANIFOLD STILL NEEDS TO BE RESET. REMOVED ACCESS PANEL 316AR AND RESET LANDING GEAR CONTROL MANIFOLD IAW MM 12-10-30. SERVICED THE HYDRAULIC RESERVOIR AND COMPLETED AND AUX. HYDRAULIC PUMP BLEED PORTION OF THE FULL BLEED IAW 680A MM CHAPTER 12-10-30.

Part: GEARBOX — CORRODED (ACCESSORY)

CORROSION ON ACCESSORY GEARBOX COVER. PRATT & WHITNEY CANADA DEVIATION LETTER DAA2021-327-PW306D1-CN0225. ACCESSORY GEARBOX TOUCH UP REPAIR.

Part: GEARBOX — CORRODED (ACCESSORY)

CORROSION ON ACCESSORY GEARBOX COVER. DEVIATION LETTER DAA2021-327-PW306D1-CN0225. ACCESSORY GEARBOX TOUCH UP REPAIR.

Part: GEARBOX — GOUGED (ACCESSORY)

GOUGE IN ACCESSORY GEARBOX. PRATT & WHITNEY CANADA DEVIATION LETTER DAA2021-326-PW306D1-CN0225. ACCESSORY GEARBOX HOUSING FRETTING.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 3,130 hrs · 2,069 cycles

CABIN EMERG LIGHT: DURING PRE FLIGHT CHECK, NO EMERGENCY LIGHTS COME ON WITH MAIN BATTERIES OFF AND SWITCH IN ARM. LIGHTS WILL COME ON WITH MAIN BATTERIES OFF AND SWITCH IN ON POSITION. UPON START UP NOTED BATTERY VOLTAGE WAS LOW. ENERGIZED THE AIRCRAFT AND CHARGED THE SYSTEM. PERFORMED OPS CHECK. GOOD. IAW CE680A AMM 33-50-00

Part: LIGHT — ABNORMAL · airframe 3,020 hrs · 2,006 cycles

EMERG EXIT SIGN/LIGHT: EMERGENCY EXIT SIGN/LIGHT AND SEAT 10 FLOOR LIGHT REMAINED ON AFTER TAKE OFF ENROUTE AND STAYED ON AFTER LANDING AND SHUTDOWN. // SIGN OFF // REMOVED AND INSTALLED COCKPIT ACCESS PANEL TO GAIN ACCESS TO #1 EMERGENCY BATTERY PACK RESET #1 EMERGENCY LIGHTING BATTERY PACK INERTIA SWITCH AND PERFORM OPS CK ON EMERGENCY LIGHTING IN REF WITH CE-680A AMM 33-50-00 OPS CHECK GOOD AND NO FURTHER DEFECTS NOTED

Part: SWITCH — MALFUNCTIONED (EMERGENCY LIGHTS) · airframe 2,922 hrs · 1,945 cycles

FORWARD EMERGENCY LIGHTS WILL NOT EXTINGUISH. FLOOR LIGHT IN FRONT OF MAIN CABIN DOOR. REPEAT WRITE UP. REMOVED RT PEDESTAL PANEL (244BR) AND RESET THE NR 1 EMERGENCY LIGHTING INERTIA SWITCH (SC001). REINSTALLED PANEL 244BR. PERFORMED A FUNCTIONAL CHECK OF THE EMERGENCY LIGHTING SYSTEM. CHECKS GOOD, REFERENCE CE-680A M/M 33-50-00.

Part: UPLOCK SWITCH — FAILED (RT MLG) · airframe 953 hrs · 664 cycles

REPEAT WRITE UP. WHILE AT CRUISE THE ANTI SKID FAIL AMBER MESSAGE APPEARED. THE QRH CHECKLIST EXTINGUISHED THE MESSAGE. THE ANTI-SKID MESSAGE APPEARED AGAIN WITH THE WOW MISCOMPARE AND GEAR DISAGREE R MESSAGE. THE QRH ANTI-SKID RESET CLEARED THE ANTI-SKID MESSAGE A SECOND TIME. ALL THE MESSAGES CLEARED PRIOR TO LANDING. // SIGNOFF// REMOVED AND REPLACED RH MLG UPLOCK SWITCH IAW CE 680A MM 32-32-00 & 52-52-25 OPS CK GOOD